Extra 330lx Quick setup guide

U.S. I N F O R M AT I O N M AN U AL
EXTRA 330LX
MANUFACTURER
EXTRA Flugzeugproduktions- und Vertriebs- GmbH
Flugplatz Dinslaken
46569 Hünxe, Federal Republic of Germany
TITLE PAGE
W A R N I N G
This is an Information Manual and may be used for general purposes only.
This Information Manual is not kept current.
It must not be used as a substitute for the official FAA approved
Airplane Flight Manual (AFM) / Pilot's Operating Handbook (POH)
required for operation of an U.S. registered airplane.

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LOGOFREVISIONS
Datesofissuefororiginalandrevisedpages:
Original ...................................... 19.February2014
Dateandsignofapproval:
ApprovedbyCSVProjectN°0010009466
DateofApproval ............................. 07.March2014
SECTION0

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Page Date
All .................................. 19.February2014
LOGOFEFFECTIVEPAGES
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INTRODUCTION
This handbook contains 9 sections, and includes the material required to be furnished to the
pilot by FAR Part 23. It also contains supplementary data supplied by EXTRA Flugzeug-
produktions-undVertriebs-GmbH.
THISMANUALISFURNISHEDTOTHECIVILAVIATIONAUTHORITIESASAPARTOFTHE
CERTIFICATIONMATERIALFORTHISMODEL.
NOTES
This Flight Manual applies only to the aircraft whose nationality and registration marks are
noted on the title page.
ThisFlight Manualis onlyvalid inconnection withthe latestapproved revision.Refer tothe
EXTRAHomepage(directlink:http://www.extraaircraft.com/techserv.asp),wherethePOH
RevisionIndexalways showsthecurrent revisionstatus.
It is the responsibility of the pilot to be familiar with the contents of this Flight Manual includ-
ingrevisionsandanyrelevantsupplements.
Pages of this Airplane Flight Manual must not be exchanged and no alterations of or
additionstotheapprovedcontentsmaybemadewithouttheEXTRAFlugzeugproduktions-
undVertriebs-GmbH/FAAapproval.
Theeditorhas the copyrightof this FlightManual and isresponsible for editionofrevisions/
amendmentsandsupplements.
Amendments,which affectthe airworthinessof theaircraftwill beannounced inthe
mandatoryServiceBulletinsissuedbythemanufacturerEXTRAFlugzeugproduktions-und
Vertriebs-GmbHcoming alongwiththe "AirworthinessDirective"(AD) publicationissuedby
theFAA. Theownerisresponsibleforincorporatingprescribedamendmentsandshould
make notes about these on the records of amendments.
ShouldthisFlightManualgetlost,informEXTRAFlugzeugproduktions-undVertriebs-GmbH,
FlugplatzDinslaken46569Hünxe,FederalRepublicofGermany.
Should this Flight Manual be found, kindly forward it to the civil board of aviation in the country
theaircraft isregistered.

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WARNINGS,CAUTIONSANDNOTES
ThefollowingdefinitionsapplytoWarnings,Cautions, andNotes:
WARNING
=> Operating procedures, techniques, etc., which could result in personal injury or
loss of life if not carefully followed.
CAUTION
=> Operating procedures, techniques, etc., which could result in damage to
equipment if not carefully followed.
N O T E
=> An operating procedures, technique, etc., which is considered essential to
emphasize.
"Shall, "Will", "Should" and "May"
The words "Shall" or "will" is used to express a mandatory requirement. The word "should" is
used to express nonmandatory provisions. The word "may" is used to express permissible.

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MAINTABLEOFCONTENTS
Section Page
1 GENERAL 1-1
2 LIMITATIONS 2-1
3 EMERGENCYPROCEDURES 3-1
4 NORMALPROCEDURES 4-1
5 PERFORMANCE 5-1
6 WEIGHT&BALANCE/EQUIPMENTLIST 6-1
7 AIRPLANE&SYSTEMSDESCRIPTIONS 7-1
8 AIRPLANEHANDLING,SERVICE&MAINTENANCE 8-1
9 SUPPLEMENTS 9-1

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Table of Contents
Paragraph Page
SECTION1
GENERAL
1.0 DESCRIPTION .................................................................................................................... 1-3
1.1 SPECIFICATION OF CLASS............................................................................................... 1-3
1.2 MANUFACTURER ............................................................................................................... 1-3
1.3 TECHNICALDATA .............................................................................................................. 1-3
1.3.1 3-ViewDrawing .................................................................................................................... 1-3
1.3.2 MainData ............................................................................................................................ 1-4
1.3.3 Wing .................................................................................................................................... 1-4
1.3.4 HorizontalTail ...................................................................................................................... 1-4
1.3.5 Elevator................................................................................................................................ 1-4
1.3.6 VerticalTail .......................................................................................................................... 1-4
1.3.7 Rudder ................................................................................................................................. 1-4
1.4 ENGINE ............................................................................................................................... 1-5
1.5 PROPELLER ....................................................................................................................... 1-5
1.5.1 Exhaust System .................................................................................................................. 1-5
1.6 FUEL ................................................................................................................................... 1-5
1.7 OIL ...................................................................................................................................... 1-5
1.8 LOADING ............................................................................................................................ 1-6
1.9 TERMINOLOGY .................................................................................................................. 1-6
1.10 SECONDARYTERMINOLOGY ............................................................................................ 1-7
1.11 CONVERSION TABLE......................................................................................................... 1-7

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1.0 DESCRIPTION
The fuselage of the EXTRA 330LX is built of a tig-welded steel-tube construction. Wings,
empennageandlandinggeararemanufacturedfromcompositematerial.
Theaircraftisatwo-seaterwiththerearcockpitequippedwithacompletesetofairplanecontrols
andinstruments.
1.1 SPECIFICATIONOFCLASS
The aircraft is certified in the acrobatic category.
1.2 MANUFACTURER
EXTRAFlugzeugproduktions-undVertriebs-GmbH,
FlugplatzDinslaken
46569Hünxe,
FederalRepublicofGermany.
1.3 TECHNICALDATA
1.3.1 3-VIEWDRAWING

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1.3.2 MAINDATA
-Length 7.20 m(23.06 ft)
-Height 2.62 m ( 8.60 ft)
-Span 8.00m (26.25ft)
- Wheel base 5.12 m(16.80 ft)
- Wheel track 1.80 m ( 5.91 ft)
1.3.3 WING
- Wing span 8.0 m (26.25 ft)
-Wing-area 10.72m²(115.39ft²)
-Airfoil Root: MA 15 S
-AirfoilTip: MA 12 S
-ChordRoot: 1.85 m (6.07 ft)
-ChordTip: 0.83 m (2.72 ft)
- MAC 1.405 m ( 4.61 ft)
-Aileronarea(withouthornbalance) 2 x 0.839 m² (2 x 9.03 ft²)
-Aileronarea(withhornbalance) 2 x 0.876 m² (2 x 9.43 ft²)
-Ailerondeflection up/down30°,tolerance±2°
1.3.4 HORIZONTALTAIL
-Span 3.20m (10.50ft)
-Area 2.56m²(27.56ft²)
-Airfoil WortmannFX71-L-150/30
1.3.5 ELEVATOR
-Area 0.768m²(8.27ft²)
-Elevator-deflection up 25°, toler. ±2°; down 25°, toler. -2°
-Trim-tab-deflection up 35°,down27°,tolerance±2°
1.3.6 VERTICALTAIL
-Area 1.55m²(16.68ft²)
-Airfoil WortmannFX71-L-150/30
1.3.7 RUDDER
-Area(withouthornbalance) 0.68 m² ( 7.32 ft²)
-Area (withhornbalance) 0.75 m² ( 8.07 ft²)
-Rudderdeflection left/right30°,tolerance±2°

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1.4 ENGINE
Manufacturer: Textron-LycomingWilliamsport PlantPA 17701USA.
Type: LycomingAEIO-580-B1A
Ratedpower: 315 HP/235 kW @ 2700 RPM
303 HP/226 kW @ 2600 RPM
286 HP/213 kW @ 2400 RPM
1.5 PROPELLER
Manufacturer: MT-PropellerEntwicklungGmbH,FederalRepublicofGermany.
Type: MTV-9-B-C/C198-25,3-bladeconstantspeed.
Alternative: MTV-14-B-C/C190-130,4-bladeconstantspeed
1.5.1 EXHAUSTSYSTEM
Manufacturer: GomolzigFlugzeug-undMaschinenbauGmbH,FederalRepublicofGermany
Complete 6 in 1 System with integrated Silencer.
1.6 FUEL
Fueltype AVGAS 100/100LL(for alternate fuelgrades see laterissues of TextronLycoming
S.I.No1070)
Minimum100/130octane.Maximum115/145octane.
Totalfuelcapacity: 189L (49.9US.gal)
- Wingtanks (2 x 60 L): 120L (31.7US.gal)
- Center tank: 60 L (15.9US.gal)
- Acro tank: 9 L (2.3 US.gal)
Usable fuel capacity in the system: 187L (49.4US.gal)
Usablefuel capacityfor acrobatic: 67 L (17.7US.gal)
1.7 OIL
Maximum sump capacity: 15.13L (16US.qt)
Minimum sump capacity: 8.51L ( 9 US.qt)
Averageambientair Mil-L6082 Mil-22851
temperature grades ashlessdispersantgrades
Alltemperatures ---- SAE 15W50 or 20W50
>27°C (80°F) SAE 60 SAE 60
>16°C (60°F) SAE 50 SAE 40 or 60
- 1°C til 32°C SAE 40 SAE 40
(30°F - 90°F)

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1.7 OIL(Cont.)
Averageambientair Mil-L6082 Mil-22851
temperature grades ashlessdispersantgrades
- 18°Ctil 21°C SAE 30 SAE 30,40 or 20W40
(0°F - 70°F)
- 18°Ctil 32°C SAE 20W50 SAE 20W50 or 15W50
(0°F - 90°F)
<-12°C(10°F) SAE 20 SAE 30 or 20W30
(single or multi - viscosity aviation grade oils see latest issue of Textron Lyc. S.I. No. 1014)
1.8 LOADING
Wingloading@ MTOW AcrobaticIII 88.62kg/m² (18.15lbs/ft²)
AcrobaticII 81.16kg/m² (16.63lbs/ft²)
AcrobaticI 76.49kg/m² (15.67lbs/ft²)
Powerloading@MTOW AcrobaticIII 4.04 kg/kW (6.65lbs/hp)
AcrobaticII 3.70 kg/kW (6.09lbs/hp)
AcrobaticI 3.49 kg/kW (5.74lbs/hp)
1.9 TERMINOLOGY
Air Speeds
CAS Calibrated Air Speed. CAS is the same as TAS
(TrueAirSpeed)instandardatmosphericconditionat sealevel
KCAS Calibratedspeedinknots
GS Groundspeed
IAS Indicatedairspeed
KIAS Indicatedspeed in knots
TAS True air speed. It's the same as CAS compensated for altitude,
temperatureanddensity
VAManeuveringspeed
VNE Neverexceedspeed
VNO Maximumstructural crusingspeed
VSStalling speed or minimum steady flight speed
VXBestangle-of-climbspeed
VYBestrate-of-climbspeed

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Meteorological terminology
ISA Internationalstandardatmosphericcondition
OAT Outsideairtemperature
1.10 SECONDARYTERMINOLOGY
fpm Feet/minute
ft Feet = 0.3048 m
in inch = 2.54 cm
m Meter
L Litres
US.gal US (liquid) gallon = 3.79 litres
US.qt US (liquid) quart = 0.946 litres
hp Horsepower(english)
h Hour
kts Knots (nm/h) = 1.852 kilometer per hour
km/h Kilometerperhour
lbs English pound = 0.4536 kg
hPa hekto Pascal
inHg Inchesofmercury
MP Manifoldpressure
PA Pressurealtitude(ft)
nm Nautical miles = 1.852 km
rpm Revolutionsperminute
CG Centerofgravity
Arm Arm isthe horizontaldistancefrom referencedatum
Moment is the product of weight of an item multiplied by its arm.

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1.11 CONVERSIONTABLE

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Section 2
Limitations
Pilot´s Operating Handbook US
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Table of Contents
Paragraph Page
SECTION2
LIMITATIONS
2.1 GENERAL............................................................................................................................ 2-3
2.2 AIR SPEED (IAS) ................................................................................................................ 2-3
2.3 CROSS-WINDCOMPONENT .............................................................................................. 2-3
2.4 ENGINE ............................................................................................................................... 2-3
2.4.1 Fuel ..................................................................................................................................... 2-3
2.4.2 EngineLimitations ............................................................................................................... 2-4
2.5 PROPELLER ....................................................................................................................... 2-5
2.6 WEIGHT LIMITS ................................................................................................................. 2-5
2.7 WEIGHTAND C.G. ENVELOPE .......................................................................................... 2-5
2.7.1 Reserved.............................................................................................................................. 2-5
2.7.2 Acrobatic Flight.................................................................................................................... 2-5
2.8 ACROBATICMANEUVERS ................................................................................................. 2-6
2.8.1 Reserved.............................................................................................................................. 2-6
2.8.2 Acrobatic Flight.................................................................................................................... 2-6
2.9 LOADFACTOR ................................................................................................................... 2-7
2.9.1 Reserved.............................................................................................................................. 2-7
2.9.2 Acrobatic Flight.................................................................................................................... 2-7
2.10 FLIGHT CREW LIMITS ....................................................................................................... 2-8
2.11 KINDS OF OPERATION LIMITS ......................................................................................... 2-8
2.11.1 StructuralTemperature/ColourLimitation .............................................................................. 2-8
2.12 MAXIMUMOPERATINGALTITUDE .................................................................................... 2-8
2.13 TIREPRESSURE ................................................................................................................ 2-8
2.14 MARKINGSANDPLACARDS ............................................................................................. 2-8
2.14.1 AircraftIdentification Plate ................................................................................................... 2-8
2.14.2 OperatingPlacards .............................................................................................................. 2-9
2.14.3 InstrumentMarkings ...........................................................................................................2-14
2.15 KINDS OF OPERATION EQUIPMENT LIST .......................................................................2-15

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Section 2
Limitations
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2.1 GENERAL
This section includes operating limitations, instrument markings, and basic placards
necessary for the safe operation of the aircraft, its engine, standard systems, and standard
equipment.The limitations includedin thissection have beenapproved bythe EASAon
behalfoftheFAA.Observanceoftheseoperating limitationsisrequiredbynationalaviation
regulations.
N O T E
In case of an aircraft equipped with specific options additional information required
for safe operation will be contained in Section 9 "Supplements".
Thisaircraft iscertified underFAA TypeCertification DataSheet N°A67EU.
Any exceedance of given limitations has to be reported by the pilot so that necessary
inspectionormaintenanceproceduresaccordingtotheMAINTENANCEMANUALEXTRA
330LXcanbeperformed.
2.2 AIRSPEED(IAS)
NeverExceedSpeed VNE 219 knots (406km/h)
Max. Structural Cruising Speed (Acro Cat. I , II, III) VNO 154 knots (285km/h)
ManeuverSpeed(AcroCat.I,II,III) VA154 knots (285km/h)
Max. Aileron Control Inputs (Acro Cat. I , II, III) up to 185 knots (343km/h)
2.3 CROSS-WINDCOMPONENT
Max.demonstrated cross-windcomponent for take-offand landingis 15knots (27km/h).
2.4 ENGINE
Engine-type: Textron-LycomingAEIO-580-B1A
Ratedmaximumpower: 235 kW (315 HP) @ 2700 rpm.
2.4.1 FUEL
Minimumgradeaviationgasoline:100/100LL;foralternatefuelgradesseelatestrevisionof
Lycoming S.I. No. 1070.
Totalfuelcapacity: 189L (49.9US.gal)
Usablefuel capacity: 187L (49.4US.gal)
Total fuel capacity for acrobatic in acro & center tank: 69L (18.2US.gal)
Usable fuel capacity for acrobatic in acro & center tank: 67L (17.7US.gal)
For acrobatic flight wing tanks must be empty.

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Limitations Pilot´s Operating Handbook US
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2.4.2 ENGINELIMITATIONS
a) Maximum Rotational Speed
Take-OffandMaximumContinuous: 2600rpm
b) Oil-temperature
-Maximum 118°C (245°F)
c) Oil capacity
- Maximum sump capacity: 15.13L (16US.qt)
- Minimum sump capacity: 8.51 L ( 9 US.qt)
d)Oil pressure
-Minimum Idling 172 kPa (25psig)
-Normal 379 - 655 kPa (55 - 95 psig)
-Starting,Warm up,TaxiandTake-Off 793 kPa (115psig)
CAUTION
It is normal for the oil pressure to "flicker" from 69 to 207 kPa (10 to 30 psig) when
going from upright to inverted flight. During knife edge flights and zero-g flights oil
pressure may drop and the oil system may not scavenge resulting in engine failure
or damage if flight is prolonged. Knife edge and zero-g flight should not exceed 10
seconds.
WARNING
If oil pressure drops to 0 kPa (psig) the propeller pitch changes automatically to
coarse (high) pitch with a corresponding decrease in RPM. Apply positive g to avoid
engine stoppage.
e) Fuel pressure
atfuelflowdivider:
-Maximum 97 kPa (14psig)
f) Cylinder head temperature
- Max 241°C (465°F)