Extra 300/SC Quick setup guide

I N F O R M AT I O N M AN U AL
E X T R A 3 0 0 / S C
MANUFACTURER
EXTRA Flugzeugproduktions- und Vertriebs- GmbH
FlugplatzDinslaken
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 EASA Approved Pilot's Operating
Handbook required for operation of the airplane.

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LOGOFREVISIONS
Datesofissuefororiginalandrevisedpages:
Original ............................29.February2008
RevisionNo.1 ..................12.February2010
RevisionNo.2 .....................10.August2010
RevisionNo.3 ................... 10.January2011
EASAApprovalNo.andDateofapproval:
EASA.A.C.08679 ....................17.July2008
ApprovedundertheauthorityofDOA
N°EASA.21J.073
ApprovedundertheauthorityofDOA
N°EASA.21J.073
ApprovedundertheauthorityofDOA
N°EASA.21J.073
Page Date: 10. January 2011

ii Page Date: 29. February 2008
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LOGOFEFFECTIVEPAGES
Page Date
Title................................ 12.February2010
i thru ii.............................. 10.January2011
iii.................................... 29.February2008
iv .................................... 12.February2010
v..................................... 29.February2008
vi .................................... 12.February2010
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2-13 .................................. 10.August2010
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6-11thru6-12................... 10.January2011
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Page Date
Page Date: 10. January 2011
SECTION0

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INTRODUCTION
Thishandbookcontains9sections,andincludesthematerialrequiredtobefurnishedtothepilot
byFAR-23.ItalsocontainssupplementarydatasuppliedbyEXTRAFlugzeugproduktions-und
Vertriebs-GmbH.
THISMANUALISFURNISHEDTOTHECIVILAVIATIONAUTHORITIESASAPARTOFTHE
CERTIFICATIONMATERIALFORTHISMODEL.
NOTES
ThisFlightManualappliesonlytotheaircraftwhosenationalityandregistrationmarksarenoted
on the title page.
ThisFlightManualisonlyvalidinconnectionwiththelatest,newEASAapprovedrevision.Refer
totheEXTRAHomepage(directlink:http://www.extraaircraft.com/techserv.asp),wherethe
POHRevisionIndexalwaysshowsthe current revision status.
It is the responsibility of the pilot to be familiar with the contents of this Flight Manual
includingrevisionsandanyrelevantsupplements.
PagesofthisAirplane Flight Manual must notbeexchangedand no alterations of oradditions
totheapprovedcontentsmaybemadewithouttheEXTRAFlugzeugproduktions-undVertriebs-
GmbH/EASAapproval.
Theeditor hasthe copyrightof thisFlight Manual and is responsible for edition of revisions/
amendmentsandsupplements.
Amendments,whichaffecttheairworthinessoftheaircraftwillbeannouncedinthemandatory
ServiceBulletinsissuedbythemanufacturerEXTRAFlugzeugproduktions-undVertriebs-GmbH
comingalongwiththe"AirworthinessDirective"(AD)publicationissuedbytheEASA. Theowner
isresponsibleforincorporatingprescribedamendmentsandshouldmakenotesabouttheseon
therecordsofamendments.
ShouldthisFlightManualgetlost,informEXTRAFlugzeugproduktions-undVertriebs-GmbH,
FlugplatzDinslaken46569Hünxe,FederalRepublicofGermany.
ShouldthisFlight Manual be found,kindlyforward it tothecivil board of aviationinthe country
theaircraftisregistered.
Page Date: 12. February 2010

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WARNINGS,CAUTIONSANDNOTES
ThefollowingdefinitionsapplytoWarnings,Cautions,and Notes:
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.
NOTE
=> An operating procedures, technique, etc., which is considered essential
to emphasize.
"Shall, "Will", "Should" and "May"
The words "shall" or "will" shall be used to express a mandatory
requirement The word "should" shall be used to express nonmandatory
provisions The word "may" shall be 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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Pilot´s Operating Handbook
EXTRA 300/SC Section 1 General
SECTION 1
GENERAL
Table of Contents
Paragraph Page
SECTION 1 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 Main Data............................................................................................................................ 1-4
1.3.3 Wing.................................................................................................................................... 1-4
1.3.4 HorizontalTail ...................................................................................................................... 1-4
1.3.5 Elevator ............................................................................................................................... 1-4
1.3.6 Vertical Tail .......................................................................................................................... 1-4
1.3.7 Rudder ................................................................................................................................ 1-4
1.4 ENGINE .............................................................................................................................. 1-4
1.5 PROPELLER ...................................................................................................................... 1-5
1.5.1 ExhaustSystem .................................................................................................................. 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 ....................................................................................................... 1-8

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EXTRA 300/SC Section 1 General
1.0 DESCRIPTION
The airframe of the EXTRA 300/SC is built of a tig-welded steel-tube construction. Wing,
empennageand landing gear aremanufactured of compositematerial. The aircraftis a single
seater.
1.1 SPECIFICATIONOFCLASS
The aircraft is certified in normal and acrobatic category.
EASA - Approval No.: EASA.A.C.08679
1.2 MANUFACTURER
EXTRA Flugzeugproduktions- und Vertriebs- GmbH,
FlugplatzDinslaken
46569 Hünxe,
Federal Republic of Germany.
1.3 TECHNICALDATA
1.3.1 3-View Drawing
Page Date: 12. February 2010

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Section 1
General Pilot´s Operating Handbook EXTRA 300/SC
1.3.2 Main Data
- Length 6.88 m (22.57 ft)
- Height 2.55 m (8.36 ft)
- Span 7.50 m (24.61 ft)
- Wheel-base 1.80 m (5.91 ft)
- Wheel-track 4.87 m (15.98 ft)
1.3.3 Wing
- Wing span 7.50 m (24.61 ft)
- Wing-area 9.81 m² (105.6 ft²)
- Airfoil Root: MA 14.9 S
Tip: MA 12 S
- Chord Root: 1.786 m (5.86 ft)
Tip: 0.830 m (2.72 ft)
- MAC 1.366 m (4.48 ft)
- Aileron area 2 x 0.876 m² (2x 9.429 ft²)
- Aileron deflection up/down 30°, tolerance ±2°
1.3.4 Horizontal Tail
- Span 2.66 m (8.73 ft)
- Area 2.13 m² (22.92 ft²)
- Airfoil NACA 0009
1.3.5 Elevator
- Area 1.04 m² (11.19 ft²)
-Elevator-deflection up/down 25°; tolerance ±1°
- Trim-tab-deflection up/down 32°, tolerance ±2°
1.3.6 Vertical Tail
- Area 1.55 m² (16.68 ft²)
- Airfoil Wortmann FX 71-L-150/30
1.3.7 Rudder
- Area 0.75 m² (8.07 ft²)
- Rudder deflection left/right 30°, tolerance +0°/-2°
1.4 ENGINE
Manufacturer Textron-Lycoming Williamsport Plant PA 17701 USA.
Type:LycomingAEIO-580-B1A
Rated power: 234.9 kW (315 HP)
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Pilot´s Operating Handbook
EXTRA 300/SC Section 1 General
1.5 PROPELLER
Manufacturer MT-Propeller Entwicklung GmbH, Federal Republic of Germany.
Type: MTV-9-B-C/C198-25 3-blade constant speed
1.5.1 Exhaust System
Standard: Complete 6 in 1 system with integrated silencer.
Manufacturer: Gomolzig Flugzeug- und Maschinenbau, West Germany
Option: Complete 6 in 1 System, stainless steel
Manufacturer: Sky Dynamics Corporation, Moneta, USA
1.6 FUEL
Type: AVGAS 100/100 LL
(for alt. fuel grades see latest issues of Textron Lyc. S.I. No 1070)
Minimum 100/130 octane. Maximum 100/130 octane
- Total fuel volume 224 L (59.2 US Gallon)
- Front center tank 54 L (14.3 US Gallon)
- Rear center tank 41 L (10.8 US Gallon)
- Acro tank 9 L ( 2.4 US Gallon)
- Wing tank 120 L (31.7 US Gallon)
- Usable fuel in the system 221 L (58.4 US Gallon)
- Usable fuel for acrobatic
(acro and center tanks) 101 L (26.7 US Gallon)
1.7 OIL
Maximum sump capacity: 16 qts.
Minimum sump capacity: 9 qts.
Average ambient air Mil-L6082 Mil-22851
temperature grades ashless dispersant grades
All temperatures ---- 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)
- 18°C til 21°C SAE 30 SAE 30,40 or 20W40
(0°F - 70°F)
- 18°C til 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)
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Section 1
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1.8 LOADING
Wing loading (Acrobatic Cat.) 79.50 kg/m² (16.29 lbs./sqf)
(Normal Cat.) 88.68 kg/m² (18.17 lbs./sqf)
Power loading (Acrobatic Cat.) 3.32 kg/kW (5.46 lbs./HP)
(Normal Cat.) 3.70 kg/kW (6.09 lbs./HP)
1.9 TERMINOLOGY
AirSpeeds
CAS Calibrated air speed. CAS is the same as TAS
(True Air Speed) in std. atmospheric condition at sea level
KCAS Calibrated speed in knots
GS Ground speed
IAS Indicated air speed
KIAS Indicated speed in knots
TAS True air speed. Is equal to CAS compensated for
altitude, temperature and density
VAManeuveringspeed
VNE Never exceed speed
VNO Maximum structural crusing speed
VSStalling speed or minimum steady flight speed
VXBest angle-of-climb speed
VYBest rate-of-climb speed
Meteorological terminology
ISA International standard atmospheric condition
OAT Outside air temperature

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EXTRA 300/SC Section 1 General
1.10 SECONDARYTERMINOLOGY
fpm Feet/minute
ft Feet = 0.3048 m
in inch = 2,54 cm
m Meter
L Litres
gal US gallon = 3.79 litres
qts US quart = 0.946 litres
hp Horse power (english)
h Hour
kts Knots (NM/h) = 1.852 kilometer per hour
km/h kilometer per hour
lbs English pound = 0.4536 kg
hPa hekto Pascal
inHg Inches of mercury
MP Manifold pressure
PA Pressure altitude (ft)
nm Nautical miles = 1.852 km
rpm Revolutions per minute
CG Center of gravity
Arm Arm is the horizontal distance from reference datum
Moment Weight of an item multiplied by its arm.

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1.11 CONVERSIONTABLE

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EXTRA 300/SC Section 2 Limitations
SECTION 2
LIMITATIONS
Table of Contents
Paragraph Page
SECTION 2 LIMITATIONS
2.1 GENERAL........................................................................................................................... 2-3
2.2 AIR SPEED (IAS) ................................................................................................................ 2-3
2.3 CROSS-WIND COMPONENT............................................................................................. 2-3
2.4 ENGINE .............................................................................................................................. 2-3
2.4.1 Fuel ..................................................................................................................................... 2-4
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 Normal Flight....................................................................................................................... 2-5
2.7.2 Acrobatic Flight.................................................................................................................... 2-5
2.8 ACROBATIC MANEUVERS................................................................................................ 2-5
2.8.1 Normal Flight....................................................................................................................... 2-5
2.8.2 Acrobatic Flight.................................................................................................................... 2-6
2.9 LOAD FACTOR................................................................................................................... 2-7
2.9.1 Normal Flight....................................................................................................................... 2-7
2.9.2 Acrobatic Flight.................................................................................................................... 2-7
2.10 KINDS OF OPERATIONAL LIMITS .................................................................................... 2-7
2.11 STRUCTUAL TEMPERATURE/COLOUR LIMITATION...................................................... 2-7
2.12 MAXIMUM OPERATINGALTITUDE................................................................................... 2-7
2.13 TIRE PRESSURE ............................................................................................................... 2-7
2.14 MARKINGSAND PLACARDS ............................................................................................ 2-7
2.14.1 Aircraft Identity Placard ....................................................................................................... 2-7
2.14.2 OperatingPlacards.............................................................................................................. 2-8
2.14.3 Instrument Markings.......................................................................................................... 2-13
2.15 KINDS OF OPERATION EQUIPMENT LIST..................................................................... 2-14
2.16 NOISE LEVEL................................................................................................................... 2-15

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Limitations
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Pilot´s Operating Handbook
EXTRA 300/SC Section 2 Limitations
SECTION 2
LIMITATIONS
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 included in this section have been approved by the EASA.
Observance of these operating limitations is required by national aviation regulations.
In case of the EXTRA 300/SC is equipped with specific options additional information
required for safe operation will be contained in Section 9 "Supplements".
EASA Approcal No.: EASA.A.C.08679
Any exceedance of given limitations have to be reported by the pilot and considered by
corresponding maintenance or inspection procedure according to MAINTENANCE MANUAL
EXTRA300/SC.
2.2 AIRSPEED (IAS)
Never Exceed Speed VNE 219 knots (406 km/h)
Max. Structural Cruising Speed VNO 154 knots (285 km/h)
Maneuver speed (Acrobatic Cat.) VA154 knots (285 km/h)
(Normal Cat.) VA138 knots (256 km/h)
2.3 CROSS-WIND COMPONENT
Max. demonstrated cross-wind component for take-off and landing is 15 knots (27 km/h).
2.4 ENGINE
Engine-type Textron-Lycoming Lycoming AEIO-580-B1A with rated maximum 315 HP @
2700 RPM.
NOTE

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Section 2
Limitations
2.4.1 FUEL
Minimum grade aviation gasoline: 100/100LL for alternate fuelgrades see latest revision of
Lyc. S.I. No. 1070.
Total fuel capacity 224 L (59.2 US Gallon).
Usable fuel capacity 221 L (58.4 US Gallon).
Acrobatic flight only with center tanks.
Total fuel capacity for acrobatic (acro & center tanks) 104 L (27.5 US Gallon).
Usable fuel capacity for acrobatic (acro & center tanks) 101 L (26.7 US Gallon).
2.4.2 ENGINELIMITATIONS
a) RPM
- Max. Take-Off 2700 RPM
- Max. Continuous 2700 RPM
b) Oil temperature
- Max 118°C 245°F
c) Oil capacity
- Maximum sump capacity: 16 qts.
- Minimum sump capacity: 9 qts.
d) Oil pressure
- Minimum Idling 172 kPa 25 psig
- Normal 379 - 655 kPa 55 - 95 psig
- Starting, Warm up
Taxi and Take-Off 793 kPa 115 psig
C A U T I O N
It is normal for the oil pressure to "flicker" from 10 to 30 psi (69 to 207 kPa) 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.
W A R N I N G
If oil pressure drops to 0 psi (kPa) 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 at inlet to fuel injector
- Max 65 psig
- Min 29 psig
- Min Idle 12 psig
f) Cylinder head temperature
- Max 241°C 465°F
Page Date: 12. February 2010