Pipistrel Virus SW 121 Owner's manual

Section 0
Foreword
Virus SW 121
Pipistrel d.o.o. Ajdovščina
Pilot
Operating Handbook
POH-121-00-40-001_A02
0-1
Pilot Operating Handbook
Virus SW 121
Registration: ____________________________
Serial No.: ____________________________
Signature: ____________________________
Authority: EASA
Stamp: ____________________________
Date of Approval: ____________________________
The airplane must be operated in compliance with
information and limitations contained herein.

Pilot
Operating Handbook
Virus SW 121
Pipistrel d.o.o. Ajdovščina
Section 0
Foreword
0-2
POH-121-00-40-001_A02
0.1 Table of Contents
Section
Contents
0
Foreword
1
General
2
Limitations
3
Emergency Procedures
4
Normal Procedures
5
Performance Data
6
Weight and Balance
7
Airplane Description
8
Handling, Servicing and Maintenance
9
Supplements
0.2 Notes
Special statements in the Airplane Flight Manual concerning the safety or
operation of the airplane are highlighted by being prefixed by one of the
following terms:
WARNING! Means that the non-observance of the corresponding
procedures lead to an immediate or significant degradation in flight safety.
CAUTION! Means that the non-observance of the corresponding
procedures leads to a minor or to a long term degradation of the flight
safety
Note: Draws the attention to any special item not directly
related to safety but which is important or unusual.

Section 0
Foreword
Virus SW 121
Pipistrel d.o.o. Ajdovščina
Pilot
Operating Handbook
POH-121-00-40-001_A02
0-3
0.3 Index of Revisions
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revision
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Pre-TC Updates
ALL
EASA
0.4 List of Effective Pages
Any revision of the present manual, except actual weighing data, must be
recorded in the table and in case of approved sections endorsed by the
Agency.
A black vertical line in the left hand margin and the revision no. will indicate
the new or amended text in the revision.
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Foreword
Virus SW 121
Pipistrel d.o.o. Ajdovščina
Pilot
Operating Handbook
POH-121-00-40-001_A02
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Section 0
Foreword
Virus SW 121
Pipistrel d.o.o. Ajdovščina
Pilot
Operating Handbook
POH-121-00-40-001_A02
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Section 1
General
Virus SW 121
Pipistrel d.o.o. Ajdovščina
Pilot
Operating Handbook
POH-121-00-40-001_A02
1-1
Section 1
General
Table of Contents
1.1 Introduction ................................................................. 2
1.2 Description .................................................................. 2
1.3 Certification Basis ....................................................... 3
1.4 Three View Drawing.................................................... 3
1.5 Dimensions and Weights ............................................ 4
1.6 Systems ...................................................................... 5
1.6.1 Powerplant ................................................................. 5
1.6.2 Propeller..................................................................... 5
1.6.3 Fuel System ............................................................... 5
1.6.4 Landing Gear ............................................................. 6
1.6.5 Ballistic Parachute Rescue System (BPRS) ............... 6
1.7 Symbols, Abbreviations and Terminology ................... 7
1.8 Conversion Table ...................................................... 11

Pilot
Operating Handbook
Virus SW 121
Pipistrel d.o.o. Ajdovščina
Section 1
General
1-2
POH-121-00-40-001_A02
1.1 Introduction
This section contains information of general interest to pilots and owners.
You will find the information useful in acquainting yourself with the airplane,
as well as in loading, fueling, sheltering, and handling the airplane during
ground operations. Additionally, this section contains definitions or
explanations of symbols, abbreviations, and terminology used throughout
this handbook.
1.2 Description
The Virus SW 121 is a two-seat aircraft of composite construction. The
aircraft is arranged as a high wing mono-plane with cantilevered wings and
a conventional empennage with a T-tail. The aircraft has a tricycle landing
gear. It is equipped with a 73,5 kW Rotax 912 S3.
The seats are side-by side with full dual flight controls and joint levers for
throttle, choke, propeller, flaps and airbrake control. Access to cockpit is via
two large gull-wing doors. Baggage area is behind the seats and accessible
via a dedicated baggage door on the left-hand side of the fuselage. The
VIRUS SW 121 is equipped with a ballistic parachute system.
The load-bearing structure of the airplane is made of carbon, glass and
aramid fiber composite material, the components of which, epoxy resin as
well as fiber materials, are in compliance with worldwide accepted aviation
specifications. The proven low-pressure wet lay-up method from the
sailplane industry is used to build the airplane structure.

Section 1
General
Virus SW 121
Pipistrel d.o.o. Ajdovščina
Pilot
Operating Handbook
POH-121-00-40-001_A02
1-3
1.3 Certification Basis
Type certification is based on EASA CS-LSA Light Sport Aircraft
Certicication Specifications. Operation of the basic version is restricted to
VFR-day and a maximum takeoff weight of 600 kg.
1.4 Three View Drawing

Pilot
Operating Handbook
Virus SW 121
Pipistrel d.o.o. Ajdovščina
Section 1
General
1-4
POH-121-00-40-001_A02
1.5 Dimensions and Weights
Basic Dimensions
Length
6.45 m
21.15 ft
Span
10.70 m
35.6 ft
Height
2.06 m
6.75 ft
Wing
Area
9.51 m²
102.4 ft²
Span
10.71 m
35.10 ft
Mean wing chord
0.898 m
2.95 ft
Horizontal Tail
Area
1.02 m²
10.9 ft²
Span
2.18 m
7.15 ft
Vertical Tail
Area
1.24 m²
13.3 ft²
Height
1.19 m
3.90 ft
Weights
Maximum takeoff
weight
600 kg
1323 lb
Design emty weight
349 kg
768 lb
Design useful load
251 kg
552 lb
Maximum baggage weight
25 kg
55 lb
Max. wing loading
63.07 kg/m²
12.92 lb/ft²

Section 1
General
Virus SW 121
Pipistrel d.o.o. Ajdovščina
Pilot
Operating Handbook
POH-121-00-40-001_A02
1-5
1.6 Systems
1.6.1 Powerplant
The engine installed is Rotax 912 S3 providing 73.5 kW takeoff power. All
limits as defined by the engine manufacturer apply. The engine can be
operated with AVGAS, MOGAS or car fuel (min RON 95; EN228 Premium
or Premium plus with max. 10% Ethanol) as by Rotax specification. The
propeller is driven by a gearbox. The gearbox is equipped with the Rotax
slipper clutch.
The engine is provided with a liquid cooling system for the cylinder heads
and a ram-air cooling system for the cylinders. There is also an oil cooling
system.
1.6.2 Propeller
The airplane is equipped with a MTV-33-1-A/170-200 made by MT-
propeller. It is a 2-blade hydraulically operated constant-speed propeller
with 1.70 m diameter. Construction is fiber reinforced wooden laminated
core.
1.6.3 Fuel System
The airplane uses two integral tanks located in the left and right wing, with
header tanks present downstream from the main tanks before the fuel
selector with three different positions: LEFT, RIGHT, OFF. Maximum
usable fuel quantity is 2 x 37.5 kg (2 x 50 L capacity).
The fuel system is designed as a pump system and provided with a
mechanical pump. A gascolator that removes water from the fuel system is
present and equipped with a 60 micron filter. An electrical pump is not
present.

Pilot
Operating Handbook
Virus SW 121
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Section 1
General
1-6
POH-121-00-40-001_A02
1.6.4 Landing Gear
The airplane has as a tricycle type fixed landing gear. The nose wheel is
steerable via rudder pedals. The main wheels are equipped with hydraulic
brakes, which are operated via toe-pedals. A parking brake lever is also
present.
1.6.5 Ballistic Parachute Rescue System (BPRS)
The airplane is equipped with a ballistic deployed parachute rescue system
GRS 6/600 SD SPEEDY. The system is not accounted for in the sense of
“alternative level of safety”. It is purely considered as a true “second
chance” beyond what is required by the certification standard. The period
for repacking of the parachute is 6 years. The date of exchange is indicated
on the parachute canister.

Section 1
General
Virus SW 121
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Pilot
Operating Handbook
POH-121-00-40-001_A02
1-7
1.7 Symbols, Abbreviations and Terminology
General Airspeed Terminology and Symbols
KCAS Knots Calibrated Airspeed is the indicated airspeed corrected
for position and instrument error. Calibrated airspeed is equal to
true airspeed in standard atmosphere at sea level.
KIAS Knots Indicated Airspeed is the speed shown on the airspeed
indicator. The IAS values published in this handbook assume no
instrument error.
KTAS Knots True Airspeed is the airspeed expressed in knots relative to
undisturbed air which is KCAS corrected for altitude and
temperature.
VGBest Glide Speed is the speed at which the greatest flight distance
is attained per unit of altitude lost with power off.
VAOperating Maneuvering Speed is the maximum speed at which
application of full control movement will not overstress the airplane.
VFE Maximum Flap Extended Speed is the highest speed
permissible with wing flaps in a prescribed extended position.
VNO Maximum Structural Cruising Speed is the speed that should not
be exceeded except in smooth air, and then only with caution.
VNE Never Exceed Speed is the speed that may not be exceeded at
any time.
VAE Maximum Airbrakes Extended Speed is the
maximum speed at which the airbrakes may be extended.
VSStalling Speed is minimum steady flight speed at which the aircraft
is controllable.

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Section 1
General
1-8
POH-121-00-40-001_A02
VSO Stalling Speed is the minimum steady flight speed at which the
aircraft is controllable in the landing configuration (100% flaps) at
the most unfavorable weight and balance.
VXBest Angle of Climb Speed is the speed at which the airplane will
obtain the highest altitude in a given horizontal distance. The best
angle-of-climb speed normally increases slightly with altitude.
VYBest Rate of Climb Speed is the speed at which the airplane will
obtain the maximum increase in altitude per unit of time. The best
rate-of-climb speed decreases slightly with altitude.
Meteorological Terminology
IMC Instrument Meteorological Conditions are meteorological
conditions expressed in terms of visibility, distance from cloud, and
ceiling less than the minima for visual flight defined in FAR 91.155.
ISA International Standard Atmosphere (standard day) is an
atmosphere where
(1) the air is a dry perfect gas,
(2) the temperature at sea level is 15° C,
(3) the pressure at sea level is 1013.2 millibars (29.92 InHg), and
(4) the temperature gradient from sea level to the altitude at which
the temperature is -56.5° C is -0.00198° C per foot and zero above
that altitude.
MSL Mean Sea Level is the average height of the surface of the sea
for all stages of tide. In this Handbook, altitude given as MSL is
the altitude above the mean sea level. It is the altitude read from
the altimeter when the altimeter’s barometric adjustment has been
set to the altimeter setting obtained from ground meteorological
sources.
OAT Outside Air Temperature is the free air static temperature
obtained from inflight temperature indications or from ground

Section 1
General
Virus SW 121
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POH-121-00-40-001_A02
1-9
meteorological sources. It is expressed in either degrees Celsius or
degrees Fahrenheit.
-Pressure Altitude is the altitude read from the altimeter when the
altimeter’s barometric adjustment has been set to 1013 mb (29.92
in.Hg) corrected for position and instrument error. In this
Handbook, altimeter instrument errors are assumed to be zero.
- Standard Temperature is the temperature that would be found at
a given pressure altitude in the standard atmosphere. It is 15° C
at sea level pressure altitude and decreases approx. 2°C for
each 1000 feet of altitude increase.
Engine Power Terminology
HP Horsepower is the power developed by the engine.
MCP Maximum Continuous Power is the maximum power that can be
used continuously.
MAP Manifold Pressure is the pressure measured in the engine’s
induction system expressed as in. Hg.
RPM Revolutions Per Minute is engine rotational speed.
Performance and Flight Planning Terminology
g One “g” is a quantity of acceleration equal to that of earth’s gravity.
-Demonstrated Crosswind Velocity is the velocity of the
crosswind component for which adequate control of the airplane
during taxi, takeoff, and landing was actually demonstrated during
certification testing.
- Service Ceiling is the maximum altitude at which the aircraft at

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Section 1
General
1-10
POH-121-00-40-001_A02
maximum weight has the capability of climbing at a 100 ft/min.
- Unusable Fuel is the quantity of fuel that cannot be used in flight.
-Usable Fuel is the fuel available for flight planning.
Weight and Balance Terminology
C.G. Center of Gravity is the point at which an airplane would balance if
suspended. Its distance from the reference datum is found by
dividing the total moment by the total weight of the airplane.
- Arm is the horizontal distance from the reference datum to the
center of an item’s gravity. The airplane’s arm is obtained by
adding the airplane’s individual moments and dividing the sum by
the total weight.
- Basic Empty Weight is the actual weight of the airplane including
all operating fix installed equipment of the airplane. The basic
empty weight includes the weight of unusable fuel and full oil.
MAC Mean Aerodynamic Chord is the chord drawn through the
centroid of the wing plan area.
LEMAC Leading Edge of Mean Aerodynamic Chord is the forward edge
of MAC aft of the reference datum.
- Maximum Gross Weight is the maximum permissible weight of
the airplane and its contents as listed in the aircraft specifications.
- Moment is the product of the items weight multiplied by its arm.
- Useful Load is the basic empty weight subtracted from the
maximum weight of the aircraft. It is the maximum allowable
combined weight of pilot, passengers, fuel and baggage.
- Reference Datum is an imaginary vertical plane from which all
horizontal distances are measured for balance purposes.
- Tare is the weight of all items used to hold the airplane on the

Section 1
General
Virus SW 121
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POH-121-00-40-001_A02
1-11
scales for weighing. Tare includes blocks, shims, and chocks. Tare
weight must be subtracted from the associated scale reading
1.8 Conversion Table
SI
US
US
SI
1 bar
14.5037 psi
1 psi
0.0689 bar
1 mm2
0.0016 in2
1 in2
625 mm2
1 cm2
0.1550 in2
1 in2
6.4510 cm2
1 daN
2.2481 lbf
1 lbf
0.4448 daN
1 g
0.0353 oz
1 oz
28.328 g
1 hPa
0.0295 in.Hg
1 in.Hg
33.898 hPa
1 kg
2.2046 lb
1 lb
0.4536 kg/min
1 kg/min
2.2046 lb/min
1 lb.min
0.4536 kg/min
1 l
0.2641 US gal
1 US gal
3.7864 l/min
1 l
1.057 US quart
1 US quart
0.9461 l
1 l/min
0.2641 US gal/min
1 US gal.min
3.7864 l/min
1 daNm
88.4956 lbf.in
1 lbf.in
0.0113 daNm
1 daNm
7.3801 lbf.ft
1 lbf.ft
0.1355 daNm
1 m
3.2809 ft
1 ft
0.3040 m
1 mm
0.0394 in
1 in
16.393 mm
1 cm3
0.06102 in3
1 in3
16.393 cm3
1 hPa
0.0145 psi
1 psi
68.965 psi

Section 2
Limitations
Virus SW 121
Pipistrel d.o.o. Ajdovščina
Pilot
Operating Handbook
POH-121-00-40-001_A02
APPROVED
2-1
Section 2
Limitations
Table of Contents
2.1 Introduction..................................................................... 3
2.2 Airspeed Limitations ....................................................... 3
2.3 Airspeed Indicator Markings ........................................... 4
2.4 Engine Limitations .......................................................... 5
2.5 Engine Instrument Markings ........................................... 6
2.6 Weight and Center of Gravity Limits ............................... 7
2.7 Occupancy...................................................................... 7
2.8 Fuel ................................................................................ 7
2.9 Oil/Coolant...................................................................... 8
2.10 Flight Load Factor Limits ................................................ 8
2.11 Maneuver Limits ............................................................. 8
2.12 Altitude Limits ................................................................. 8
2.13 Temperature Limits......................................................... 9
2.14 Minimum Flight Crew...................................................... 9
2.15 Kinds of Operation.......................................................... 9
2.16 Operational Restrictions ................................................. 9
2.16.1 Restrictions for Aerotowing Operations ................ 10

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Section 2
Limitations
APPROVED
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POH-121-00-40-001_A02
2.17 PFD / Autopilot Restrictions.......................................... 10
2.18 Placards........................................................................ 11
2.18.1 Placards (External)................................................... 11
2.18.2 Placards (Engine Compartment) .............................. 13
2.18.3 Placards (Instrument Panel) ..................................... 13
2.18.4 Placards (Center Console) ....................................... 15
2.18.5 Placards (Cabin) ...................................................... 16
2.18.6 Placards (Ballistic Parachute Rescue System) ......... 18