Pipistrel VIRUS SW 600 D Owner's manual

VIRUS SW 600 D
equipped with Rotax 912 iS Series engine
Document No.: SPOH-127-00-41-001
REVISION A00
Date of Issue: November 22nd, 2019
Aircraft Registration Number:
Aircraft Serial Number:
PIPISTREL VERTICAL SOLUTIONS d.o.o.
Vipavska cesta 2
SI-5270 Ajdovščina
Slovenia
Tel: + 386 5 36 63 873
Fax: + 386 5 36 61 263
Email: [email protected]
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.
PILOT OPERATING
HANDBOOK SUPPLEMENT

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SPOH-127-00-41-001
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Virus SW 600 D - equipped with Rotax 912 iS Series Engine
The airplane must be operated in compliance with
information and limitations contained herein.
Pilot Operating Handbook Supplement

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POH
SECTION
SUPPLEMENT
CONTENTS
0FOREWORD
1GENERAL
2LIMITATIONS
3EMERGENCY PROCEDURES
4NORMAL PROCEDURES
5PERFORMANCE DATA
-
7AIRPLANE DESCRIPTION
-
Table of contents
Online updates, service notice tracking
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login to our technical publication portal using the following:
Username: owner1
Password: ab2008

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This supplement, supplied with the airplane at the time of delivery from
Pipistrel, contains information applicable to the Virus SW 600 D airplane,
equipped with the Rotax 912 iS Series engine and designated by the serial
number and registration number in cover page. All information is based on
data available at the time of publication.
Content included in this supplement, if not dierently specified replaces
the corresponding content in the original POH.
Revision tracking, filing and identifying
Pages to be removed or replaced in this pilot operating handbook supple-
ment (SPOH) are determined by the log of effective pages located in this sec-
tion. This log contains the page number and revision number for each page
within the SPOH. As revisions to the SPOH occur, the revision number on the
affected pages is updated and the page number in the log is highlighted with
bold font type. When two pages display the same page number, the page
with the latest revision shall be used in the SPOH.
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.
Revised material is marked with a vertical 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 document is revised. A list of revisions
is located at the beginning of the log of effective pages. Pipistrel is not re-
sponsible for technical changes/updates to OEM manuals supplied with the
aircraft (eg. radio, transponder, GPS, etc.).
USING THIS SUPPLEMENT

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PAGE
Doc.
Rev. Description Reason for revision Aected pages Authority
A00 Initial /ALL SLO.DOA.002
Index of document revisions

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SECTION
1

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PART SUBJECT PAGE NUMBER
1.2 DESCRIPTION 1-3
1.6
SYSTEMS 1-4
Powerplant
Fuel System
SECTION 1 – GENERAL
TABLE OF CONTENTS

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SECTION 1
GENERAL
1.2. DESCRIPTION
The Virus SW 600 D is a two-seat aircraft of composite construction. The
aircraft is arranged as a high wing mono-plane with cantilevered wings, con-
ventional T-tail empennage and tricycle landing gear. It is equipped with a
73,5 kW Rotax 912 iS Series engine.
The cabin incorporates side-by-side seating and two large gull-wing doors.
The flight control system, which consists of various levers, pedals, bellcranks
and pushrods, is designed in a way to ensure full flight control from either
side of the cabin. A centrally-located qudrant incorporates two levers for
throttle and propeller pitch control. The baggage area is behind the seats
and accessible via a dedicated door on the left-hand side of the fuselage.
The VIRUS SW 600 D is equipped with a ballistic parachute system.
The load-bearing structure of the airplane is made of carbon, glass and ara-
mid fiber composite material, the components of which, epoxy resin as well
as fiber materials, are in compliance with worldwide accepted aviation spec-
ifications. The proven low-pressure wet lay-up method from the sailplane
industry is used to build the airplane structure.
The airplane is not approved for intentional spins and aerobatics.

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SECTION 1
GENERAL
1.6 SYSTEMS
1.6.1 POWERPLANT
The engine installed is Rotax 912 iS Series providing 73.5 kW takeo power.
All limits as defined by the engine manufacturer apply. The engine can be
operated with AVGAS 100LL or MOGAS (min. RON 95 antiknock properties
and max. 10% ethanol content) as by Rotax specification. The propeller is
driven by a gearbox which is equipped with a Rotax slipper clutch.
The engine is both ram air and liquid-cooled, while a separate, oil-based
lubrication system provide some additional cooling.
1.6.3 FUEL SYSTEM
The airplane has two integral tanks located in the left and right wing. Collec-
tor tanks are present downstream from the main tanks and a fuel selector
with three dierent positions: LEFT, RIGHT and OFF. Maximum usable fuel
quantity is 2 x 35.6 kg / 2 x 49.5 L (2 x 36 kg / 2 x 50 L max tank capacity).
The fuel system incorporates with two electrical pumps (main and auxiliary)
positioned in the baggage compartment. A gascolator that removes water
from the fuel system is present, equipped with filter and drain.
See Section 7 – Airplane description for additional details.

SECTION
2

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SECTION 2
LIMITATIONS
PART SUBJECT PAGE NUMBER
2.4 ENGINE LIMITATIONS 2-3
2.5 ENGINE INSTRUMENT MARKINGS 2-4
2.8 FUEL 2-4
2.15 KINDS OF OPERATIONS 2-5
2.17 PLACARDS 2-6
Placards (External)
SECTION 2 – LIMITATIONS
TABLE OF CONTENTS

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SECTION 2
LIMITATIONS
2.4 ENGINE LIMITATIONS
Engine (Rotax 912 iS Series) (all limitations in OEM documentation apply)
Maximum Power rating 73.5 kW / 5800 RPM
Max 5 min
Maximum Continuous Power 72 kW/5500 RPM for iS/iSc Sport
(or 69 kW for iS version)
Normal RPM 1400 - 5500 RPM (5800 RPM for 5 min)
Maximum RPM 5800 RPM
Minimum Oil Pressure 0.8 bar (11.6 psi)
Normal Oil Pressure 2.0 – 5.0 bar (29 - 72.5 psi)
Maximum Oil Pressure
7.0* bar (101.5 psi)
*permissible for a short period after cold
start
Minimum Oil Temperature 50° C (122° F)
Maximum Oil Temperature 130° C (266° F)
Minimum Coolant Temperature -20° C (-4° F)
Maximum Coolant Temperature 120° C (248° F)
Maximum Exhaust Gas Temperature 950° C (1742° F)
Minimum fuel pressure 2.9 bar (42 psi)
Maximum fuel pressure 3.1 bar (45 psi)
Minimum Manifold Temperature 60° C (140° F) in flight

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SECTION 2
LIMITATIONS
2.5 ENGINE INSTRUMENT MARKINGS
INSTRUMENT
RANGE
RED LINE GREEN ARC YELLOW ARC RED LINE
MINIMUM NORMAL CAUTION MAXIMUM
Tachometer
(0 - 6000 RPM) 1680 1750-5500 5500-5800 5800
Coolant Temp.
(50 - 130° C) –– –– –– 120° C
Exhaust Gas Temp.
(400 - 930° C) 420° C 550-900° C 900-950° C 950° C
Manifold Pressure
(0 – 35 inHg) –– 0-29.92 inHg 28-29.92 inHg 29.92 inHg
Fuel Flow
(0 – 30 l/h) –– 5-25 l/h –– ––
Fuel Pressure
(0 – 3.5 bar) 2.3 bar 2.8-3.1 bar 3.1-3.3 bar 3.3 bar
Oil Temperature
(0 - 140° C) –– 50-110° C 110-130° C 130° C
Oil Pressure
(0 - 7.8 bar) 1.0 bar 1.4-6.2 bar 6.2-6.6 bar 7.0 bar (Cold)
Voltmeter
(10 - 16 V) 10 V 11.8–14.4 V 14.4–14.7 V 14.7 V
Ammeter
(-40 – 40 A) –– Green line at 20 A –– ––
2.8 FUEL
Approved fuels include MOGAS or AVGAS 100LL, with max. 10% ethanol
and the following antiknock properties: min. RON 95 (min. AKI 91). As by
Rotax specification: SI-912 I-001R5 Selection of suitable operating fluids for
RotaxEngine (latest revision).
Total fuel capacity 100 liters / 72 kg
Total fuel each tank 50 liters / 36 kg
Total usable fuel (all flight conditions) 99 liters / 71.3 kg
Maximum allowable fuel imbalance 50 liters / 36 kg
NOTE: Operation with leaded fuels (including AVGAS) results in shorter oil
filter replacement intervals of 50 hours.

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SECTION 2
LIMITATIONS
NOTE: Unusable fuel is 0.5 liters per tank.
2.15 KINDS OF OPERATION
The airplane is approved for the following operations:
See original POH
NOTE: The airplane must be equipped according to the MLE for the planned
kind of operation, see MINIMUM LIST OF EQUIPMENT TABLE.
2.15.1 MINIMUM LIST OF EQUIPMENT
SYSTEM,
INSTRUMENT,
EQUIPMENT
MLE  REQUIRED FOR KIND OF
OPERATION
VFR
Day
VFR
Night IFR
VHF COM / (NAV) — — —
Battery 1 — —
Ammeter/Voltmeter Indication 1* — —
Emergency Locator Trans. — — —
Flap System 1 — —
Pitch Trim Indicator — — —
Pitch Trim System — — —
Stall Warning System 1* — —
Fuel Quantity Indicator 2 — —
Fuel Selector Valve 1 — —
Anti-Collision Lights — — —
Oil Quantity Indicator 1 — —
Oil Temperature Indication 1* — —
Parachute Rescue System — — —
Airplane Flight Manual/POH 1 — —
Navigation Lights — — —
Landing Light — — —
Airspeed Indicator 1 — —
Altimeter 1 — —
Magnetic Compass 1 — —
Pitot System 1 — —
Static System 1 — —
PFD Attitude Indication — — —
PFD Airspeed Indication — — —
PFD Altitude Indication — — —
PFD Heading Indication — — —

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SECTION 2
LIMITATIONS
PFD Slip/Skid Indication — — —
Vertical Speed Indicator — — —
Multi-Function Display 1 — —
Coolant Temperature Indication 1* — —
EGT Indication 1* — —
Fuel Flow Indication — — —
Fuel Pressure Indication 1*
Fuel Pumps 2
Manifold Pressure Indication 1* — —
Oil Pressure Indication 1* — —
* The indication is integrated into the Dynon system/display
2.17 PLACARDS
2.17.4 PLACARDS CENTER CONSOLE
Next to throttle lever (this placard replaces the choke and throttle placard):

SECTION
3

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PART SUBJECT PAGE NUMBER
3.3
GROUND EMERGENCIES 3-3
Engine Fire During Engine Start
Emergency Engine Shutdown On Ground
Emergency Ground Egress
3.4
IN-FLIGHT EMERGENCIES 3-4
Engine Failure at Takeo (Low Altitude)
Engine Failure in Flight
Engine Start in Flight
Engine Partial Loss of Power
Low Oil Pressure
Propeller Governor Failure
FIRE IN FLIGHT 3-9
Smoke in the Cockpit
3.5 Engine Fire in Flight
Wing Fire in Flight
Cockpit Fire in Flight
3.7 BPRS DEPLOYMENT 3-11
3.8 LANDING EMERGENCIES 3-13
Emergency Landing without Engine Power
Ditching
Landing without Elevator Control
Landing with a Defective Main Landing Gear Tire
Landing with Defective Brakes
3.10 GENERATOR / ELCTRICAL SYSTEM FAILURE 3-15
3.14 BATTERY OVERVOLTAGE / MALFUNCTION 3-16
3.17 CHECKLIST - EMERGENCY PROCEDURES 3-19
SECTION 3 – EMERGENCY PROCEDURES
TABLE OF CONTENTS

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SECTION 3
EMERGENCY PROCEDURES
APPROVED
3.3 GROUND EMERGENCIES
3.3.1 ENGINE FIRE DURING ENGINE START
A fire during engine start may be caused by fuel igniting in the fuel induc-
tion system. If this occurs, attempt to draw the fire back into the engine by
continuing to crank the engine.
1Fuel Selector OFF
2Starter KEEP CRANKING
3Throttle Lever Full Forward
Once fire is estinguished:
4LANE A/B switches OFF
5Fuel pumps (main and aux) OFF
6Master OFF
If flames persist, perform Emergency Ground Egress procedure.
3.3.2 EMERGENCY ENGINE SHUTDOWN ON GROUND
1Throttle Lever IDLE
2Fuel Selector OFF
3LANE A/B switches OFF
4Master Switch OFF
3.3.3 EMERGENCY GROUND EGRESS
1Engine SHUTDOWN
2Parking brake ENGAGED
3Seat belts RELEASE
4Airplane EXIT
While exiting the airplane, make sure evacuation path is clear of other air-
craft, spinning propellers, and other hazards. If the engine is left running, set
the parking brake prior to evacuating the airplane.

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SECTION 3
EMERGENCY PROCEDURES
3.4 INFLIGHT EMERGENCIES
3.4.1 ENGINE FAILURE AT TAKEOFF LOW ALTITUDE
If the engine fails immediately after take-o, abort by landing on the run-
way. If this is not possible and altitude is not sucient enough to restart the
engine, lower the nose to maintain airspeed and establish a glide attitude.
In most cases, the landing should be made straight ahead, turning only to
avoid obstructions. After establishing a glide for landing, perform as many of
the checklist items as time permits.
WARNING:!!If a turn back to the runway is elected, be very careful not to
stall the airplane.
1Best Glide or Landing Speed (as appropriate)
ESTABLISH - see
Ch.3 airspeed
for emergency
operations
2Fuel Selector OFF
3LANE A/B switches OFF
4Fuel pumps (main and aux) Both OFF
5Flaps AS REQUIRED
If time permits:
1Throttle Lever IDLE
2Master Switch OFF
3Seat Belts ENSURE SECURED
3.4.2 ENGINE FAILURE IN FLIGHT
If the engine fails at altitude, pitch as necessary to establish best glide speed
(130 km/h or 70 kts IAS). While gliding toward a suitable landing area, at-
tempt to identify the cause of the failure and correct it. If altitude or terrain
does not permit a safe landing, BPRS deployment may be required.
1Best Glide Speed ESTABLISH,
130 km/h (70 kts) IAS