Extra 300S Information Manual

TITLE P AGE

I N F O R M A T I O N M A N U A L

E X T R A 3 0 0 S

MANUFACTURER

EXTRA Flugzeugproduktions- und Vertriebs- GmbH

Flugplatz Dinslaken

46569 Hünxe, Federal Republic of Germany

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 Pilot's Operating

Handbook required for operation of the airplane.

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MAIN TABLE OF CONTENTS

Section Page

0 PUBLICATION GUIDANCE..............................................................................................0-1

1 GENERAL......................................................................................................................... 1-1

2 LIMITATIONS ...................................................................................................................2-1

3 EMERGENCY PROCEDURES.........................................................................................3-1

4 NORMAL PROCEDURES ................................................................................................ 4-1

5 PERFORMANCE.............................................................................................................. 5-1

6 WEIGHT AND BALANCE AND EQUIPMENT LIST.......................................................... 6-1

7 DESCRIPTION AND OPERATION OF AIRCRAFT AND SYSTEMS................................ 7-1

8 HANDLING, SERVICING AND MAINTENANCE .............................................................. 8-1

9 SUPPLEMENTS ...............................................................................................................9-1

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THIS HANDBOOK SHALL ALWAYS BE CARRIED ON BOARD DURING FLIGHT.
PILOTS OPERATING HANDBOOK PREPARED THIS MANUAL IS FURNISHED TO

BY: THE CIVIL AVIATION AUTHORITIES

AS A PART OF THE CERTIFICATION-

EXTRA Flugzeugproduktions- und Vertriebs- GmbH MATERIAL FOR THIS MODEL.

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Publication Guidance

Section 0

SECTION 0

PUBLICATION GUIDANCE

Table of Contents

Paragraph Page

SECTION 0 PUBLICA TION GUIDANCE

1 INTRODUCTION.................................................................................................................. 0-3

2 NOTES ................................................................................................................................ 0-3

3 WARNINGS, CAUTIONS AND NOTES................................................................................ 0-4

4 LOG OF EFFECTIVE P AGES.............................................................................................. 0-5

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Publication Guidance

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1 INTRODUCTION

This handbook contains 10 sections, and includes the material required to be
furnished to the pilot by FAR Part 23 . It also contains supplementary data

supplied by EXTRA Flugzeugproduktions- und Vertriebs- GmbH .

2 NOTES

Publication Guidance

Section 0

2.1 This Flight Manual applies only to the aircraft whose nationality and
registration marks are noted on the title page.

2.2 It is the responsibility of the pilot to be familiar with the contents
of this Flight Manual including revisions and any relevant supplements.

2.3 Pages of this Airplane Flight Manual must not be exchanged and no alterations
of or additions to the approved contents may be made without theEXTRA Flugzeug­produktions- und Vertriebs- GmbH/LBA approval.
The editor has the copyright of this Flight Manual and is responsible for edition of

revisions/amendments and supplements.

2.4 Amendments, which affect the airworthiness of the aircraft will be
announced in the publication Lufttüchtigkeitsanweisung (airworthiness
directive) issued by LBA, Luftfahrt-Bundesamt, or by the manufacturer

EXTRA Flugzeugproduktions- und Vertriebs- GmbH. The owner is responsible for incorporating
prescribed amendments and should make notes about these on the records
of amendments.

2.5 Should this Flight Manual get lost, inform EXTRA Flugzeugproduktions- und Vertriebs- GmbH,
Dinslaken 46569 Hünxe, Federal Republic of Germany.

2.6 Should this Flight Manual be found, kindly forward it to the civil
board of aviation in the country the aircraft is registered.

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Section 0
Publication Guidance

3 WARNINGS, CAUTIONS AND NOTES

The following definitions apply to Warnings, Cautions, and Notes:

=> Operating procedures, techniques, etc which could result in personal
injury or loss of life if not carefully followed.

=> Operating procedures, techniques, etc , which could result in damage to
equipment if not carefully followed.

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WARNING

CAUTION

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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4 LOG OF EFFECTIVE PAGES

Publication Guidance

Section 0

Dates of issue for original and revised pages:

Original .............................. 13. March 1993

Revision No. 1 .................. 6. October 1994

Revision No. 2 ..................... 26. June 1997

Edition No. 2 .........................20. April 2002

Rev. No. 1, 2nd Ed........... 31. January 2006

Rev. No. 2, 2nd Ed...... 20. September 2006

Date and sign of approval:

LBA approved..................... 19. March 1993

LBA approved................... 24. January 1995

LBA approved.................... 27. August 1997

LBA approved...................30. October 2002

EASA Approval N° ......... EASA.A.A.01169

Date of Approval ................... 8. March 2006

EASA Approval N° ......... EASA.A.A.01319

Date of Approval ............ 20. November 2006

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Section 0
Publication Guidance

LOG OF EFFECTIVE PAGES (cont.)

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Page Date

Title.................................. 31. January 2006

i ............................................ 20. April 2002

ii....................................... 31. January 2006

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Section 1

General

SECTION 1

GENERAL

Table of Contents

Paragraph Page

SECTION 1 GENERAL

1.0 DESCRIPTION.................................................................................................................... 1-3

1.1 SPECIFICA TION OF CLASS .............................................................................................. 1-3

1.2 MANUFACTURER .............................................................................................................. 1-3

1.3 TECHNICAL DATA.............................................................................................................. 1-3

1.3.1 3-View Drawing ................................................................................................................... 1-3

1.3.2 Main Data............................................................................................................................ 1-4

1.3.3 Wing.................................................................................................................................... 1-4

1.3.4 Horizontal Tail ...................................................................................................................... 1-4

1.3.5 Elevator ............................................................................................................................... 1-4

1.3.6 Vertical Tail .......................................................................................................................... 1-4

1.3.7 Rudder ................................................................................................................................ 1-4

1.4 ENGINE .............................................................................................................................. 1-5

1.5 PROPELLER ......................................................................................................................1-5

1.5.1 Exhaust Systems (Optional)................................................................................................ 1-5

1.6 FUEL................................................................................................................................... 1-5

1.7 OIL ...................................................................................................................................... 1-5

1.8 LOADING............................................................................................................................ 1-6

1.9 TERMINOLOGY ................................................................................................................. 1-6

1.10 SECONDARY TERMINOLOGY .......................................................................................... 1-7

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Section 1
General

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1.0 DESCRIPTION

This description belongs to aircraft type EXTRA 300/S with nationality and registration
marks:

Manufacturing
The airframe is built of tig-welded steel-tube construction. Wings, rudder and landing gear are

manufactured of composite material.
The aircraft is a one-seater.

1.1 SPECIFICATION OF CLASS

The aircraft is certified in normal and acrobatic category.
LBA - Certificate No. 1086.

Section 1

General

1.2 MANUFACTURER

Manufacturer EXTRA Flugzeugproduktions- und Vertriebs- GmbH, Flugplatz Dinslaken
46569 Hünxe, Federal Republic of Germany.

1.3 TECHNICAL DATA

1.3.1 3-View Drawing

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Section 1
General

1.3.2 Main Data

- Length 6,65 m (21,82 ft)

- Height 2,62 m (8,60 ft)

- Span 7,50 m (24,61 ft)

- Wheel-base 1,80 m (5,91 ft)

- Wheel-track 4,75 m (15,58 ft)

1.3.3 Wing

- Wing span 7,5 m (24,61 ft)

- Wing-area 10,44 m² (112,38 ft²)

- Airfoil Root: MA 15 S. Tip: MA 12 S

- Chord Root: 1,85 m (6,07 ft)

- MAC 1,44 m (4,72 ft)

- Aileron area 2 x 0,830 m² (2 x 8,93 ft²)

- Aileron deflection ± 30°, tolerance ± 2°

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Tip: 0,93 m (3,05 ft)

1.3.4 Horizontal Tail

- Span 3,20 m (10,50 ft)

- Area 2,56 m² (27.56 ft²)

- Airfoil Wortmann FX 71-L-150/30

1.3.5 Elevator

- Area 0,77 m² (8,29 ft²)

- Elevator-deflection up 26°; down 26°; tolerance ± 2°

- Trim-tab-deflection ± 15°, tolerance ± 2°

1.3.6 Vertical Tail

- Area 1,39 m² (14,96 ft²)

- Airfoil Wortmann FX 71-L-150/30

1.3.7 Rudder

- Area 0,51 m² ( 5,49 ft²)

- Rudder deflection left 30°; right 30°; tolerance ± 2°

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1.4 ENGINE

Manufacturer Textron-Lycoming Williamsport Plant PA 17701 USA.
a) Type Lycoming AEIO-540-L1B5
b) Type Lycoming AEIO-540-L1B5D

Rated power: 300HP @ 2700RPM, 270HP @ 2400RPM

1.5 PROPELLER

Manufacturer MT-Propeller Entwicklung GmbH, Federal Republic of Germany.
a)Type MTV-9-B-C/C 200-15 3-blade constant speed.
b)Type MTV-14-B-C/C 190-174-blade constant speed.

1.5.1 Exhaust Systems (Optional)

Manufacturer Gomolzig Flugzeug- und Maschinenbau GmbH, Federal Republic of Germany
Exhaust Silencer for standard system: PN: EA 300 NSD, GO3-606500.
Complete 6 in 1 System with integrated Silencer: PN: EA 300-606000

Section 1

General

1.6 FUEL

1.7 OIL

Fuel type AVGAS 100/100 LL (for alternate fuel grades see later issues of Textron Lyc. S.I.
No 1070)

Minimum 100/130 octane. Maximum 115/145 octane
Total fuel volume 171 litres (45,1 US Gallon)

- Wingtanks (2 x 60 l) 120 litres (31.7 US Gallon)

- Center tank 42 litres (11,1 US Gallon)

- Acro tank 9 litres (2,3 US Gallon)
Usable fuel in the system 169 litres (44,6 US Gallon)

Usable fuel for acrobatic (acro and center tank) 49 litres (12.9 US Gallon)

Maximum sump capacity: 16 qts.
Minimum sump capacity: -Acrobatics: 12 qts.

-Normal: 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)

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Section 1
General

1.7 OIL (Continuation)

Average ambient air Mil-L6082 Mil-22851
temperature grades ashless dispersant grades

- 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)

1.8 LOADING

Wing loading 88,1 kg/m² Normal

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78,5 kg/m² Acrobatic

Power loading 3,07 kg/hp Normal

1.9 TERMINOLOGY

Air Speeds

CAS Calibrated Air Speed. CAS is the same as TAS

KCAS Calibrated speed in knots
GS Ground speed
IAS Indicated air speed
KIAS Indicated speed in knots
TAS True air speed. It's the same as CAS compensated for

VA Maneuvering speed
VNE Never exceed speed

2.73 kg/hp Acrobatic

(True Air Speed) in std. atmospheric condition at sea level

altitude, temperature and density

VNO Maximum structural crusing speed
VS Stalling speed or minimum steady flight speed
VX Best angle-of-climb speed
VY Best rate-of-climb speed

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Meteorological terminology

ISA International standard atmospheric condition
OAT Outside air temperature

1.10 SECONDARY TERMINOLOGY

FPM Feet/minute
ft Feet = 0.3048 m
inch inch = 2,54 cm
m Meter
L Litres
Gal US gallon = 3.79 litres

Section 1

General

Qts US quart = 0.946 litres
hp Horse power (english)
h Hour
kts Knots (NM/h) = 1.852 kilometer per hour
Lbs English pound = 0.4536 kg
hPA hekto Pascal
IN HG 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 is the product of weight of an item multiplied by its arm.

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General

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Section 2

Limitations

SECTION 2

LIMITATIONS

Table of Contents

Paragraph Page

SECTION 2 LIMIT A TIONS

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 Engine Limitations ...............................................................................................................2-4

2.5 PROPELLER ......................................................................................................................2-5

2.6 WEIGHT LIMITS................................................................................................................. 2-5

2.7 WEIGHT AND C.G . ENVELOPE ......................................................................................... 2-5

2.7.1 Normal Flight....................................................................................................................... 2-5

2.7.2 Acrobatic Flight.................................................................................................................... 2-5

2.8 ACROBA TIC MANEUVERS................................................................................................ 2-5

2.8.1 Normal Flight....................................................................................................................... 2-5

2.8.2 Acrobatic Flight.................................................................................................................... 2-6

2.9 LOAD F ACTOR................................................................................................................... 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 OPERA TING ALTITUDE................................................................................... 2-7

2.13 TIRE PRESSURE ............................................................................................................... 2-7

2.14 MARKINGS AND PLACARDS ............................................................................................ 2-7

2.14.1 Aircraft Identity Placard .......................................................................................................2-7

2.14.2 Operating Placards.............................................................................................................. 2-8

2.14.3 Instrument Markings.......................................................................................................... 2-11

2.15 KINDS OF OPERATION EQUIPMENT LIST..................................................................... 2-12

2.16 NOISE LEVEL................................................................................................................... 2-13

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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 included in this section have been approved by the Luftfahrt­Bundesamt (LBA). Observance of these operating limitations is required by national aviation
regulations.

In case of an aircraft is equipped with specific options additional information required for
safe operation will be contained in Section 9 "Supplements".

Section 2

Limitations

SECTION 2

LIMITATIONS

NOTE

Instrument markings and placards are provided for the acrobatic category only; for normal
category refer to corresponding limitations. This aircraft is certified under LBA-Flugzeug­kennblatt Nr. 1086, Type Certification Data Sheet (T.C.D.S.).

Any exceedance of given limitations have to be reported by the pilot and considered by
corresponding maintenance or inspection procedure according to SERVICE MANUAL EA

300/S.

2.2 AIR SPEED (IAS)

Never Exceed Speed VNE 220 knots
Max. Structural Cruising Speed VNO 158 knots
Maneuver speed (Normal) VA 140 knots
Maneuver speed (Acro) VA 158 knots

2.3 CROSS-WIND COMPONENT

Max. demonstrated cross-wind component for take-off
and landing 15 knots.

2.4 ENGINE

Engine-type Textron-Lycoming AEIO-540-L1B5 / AEIO-540-L1B5D with rated maximum
300 HP @ 2700 RPM.

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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 171 liters (45.1 US Gallon).
Usable fuel capacity 169 liters (44.6 US Gallon).
For acrobatic flight wing tanks must be empty.
Total fuel capacity for acrobatic 51 liters (13.4 US Gallon) in acro tank.
Usable fuel capacity for acrobatic 49 liters (12.9 US Gallon) in acro tank.

2.4.2 ENGINE LIMITATIONS

a) Tachometer gauge

-Max. Take-Off (max 5 min) 2700 RPM

-Max. Continuous 2400 RPM

If not stated somewhere else (refer to section: 4.12 Acrobatic Maneuvers) the aircraft may
be operated in acrobatic maneuvers up to 2700 RPM.

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NOTE:

b) Oil-temperature gauge

-Max 245°F

c) Oil capacity

-Maximum sump capacity: 16 qts.

-Minimum sump capacity: -Acrobatic: 12 qts.

-Normal: 9 qts.

d) Oil pressure

-Minimum Idling 25 Psi

-Normal 55 - 95 Psi

-Starting, Warm up
Taxi and Take-Off 115 Psi

C A U T I O N

It is normal for the oil pressure to "flicker" from 10 to 30 psi 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 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

-Max 40 Psi

-Min 18 Psi

-Min Idle 12 Psi

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f) Cylinder head temperature

-Max 500°F

2.5 PROPELLER

MT-Propeller Entwicklung GmbH, Federal Republic of Germany
a) Type MTV-9-B-C-/C 200-15
b) Type MTV-14-B-C-/C 190-17

-Max. Take-Off (max 5 min) 2700 RPM

-Max. Continuous 2400 RPM *

If not stated otherwise (refer to section: 4.12 Acrobatic Maneuvers) the aircraft may be
operated in acrobatic maneuvers up to 2700 RPM.

2.6 WEIGHT LIMITS

Max. allowed empty weight:

-Normal category 711 kg (1567 lbs)

-Acrobatic category 697 kg (1536 lbs)

NOTE:

NOTE *

Section 2

Limitations

Max. allowed T/O weight:

-Normal category 920 kg (2028 lbs)

-Acrobatic category 820 kg (1808 lbs)

Max allowed landing weight: 920 kg (2028 lbs)

2.7 WEIGHT AND C.G. ENVELOPE

Vertical reference = fire-wall.
Horizontal reference = upper longerons in cockpit.

2.7.1 NORMAL FLIGHT

Max T/O Weight: forward C.G. rear C.G.
920 kg (2028 lbs) 48.9 cm (19,3") 71,4 cm (28,1")
(and below)

2.7.2 ACROBATIC FLIGHT

Max T/O weight: forward C.G. rear C.G.
820 kg (1808 lbs) 48.9 cm (19,3") 71,4 cm (28,1")
(and below)

2.8 ACROBATIC MANEUVERS

2.8.1 NORMAL FLIGHT

All acrobatic maneuvers are prohibited except stall, chandelle, lazy eight and turns up to 60
degrees bank angle.

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Section 2
Limitations

Pilot´s Operating Handbook

2.8.2 ACROBATIC FLIGHT

The plane is designed for unlimited acrobatics (wing tanks must be empty). Inverted flight
maneuvers are limited to max 4 min. Recommended basic maneuver entry speeds are
listed in the following list:

Recommended entry

Maneuvers speeds Symbol Remarks

min KIAS max KIAS

Segment:

Horizontal Line V

s

V

ne

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45°climbing 80 V
90° up 158 V
45° diving V
90° diving V

s

s

ne

ne

V

ne

V

ne

reduce throttle

reduce throttle
1/4 Loop climb. 100 190
Looping 100 190
Stall turn 100 190
Aileron roll 80 158 full deflection
Snap roll 80 140
"Tail slide" 100 190
Spin V
Inverted spin V

s

s

Knife edge >150 < 10 s
Inverted Flight >V

s

190 < 4 min

CAUTION

Particular caution must be exercised when performing maneuvers at speeds above
Va (158 KIAS). Large or abrupt control inputs above this speed may impose
unacceptably high loads which exceed the structural capability of the aircraft.

N O T E

For Acrobatic Maneuvers see Section 4. All maneuvers can be performed in positive and
negative flight attitude.

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2.9 LOAD FACTOR

2.9.1 NORMAL FLIGHT

+ 6 g / -3 g for MTOW 920 kg (2028 lbs)

2.9.2 ACROBATIC FLIGHT

+ 10 g / - 10 g for MTOW 820 kg (1808 lbs)

2.10 KINDS OF OPERATIONAL LIMITS

Only VFR flights at day are allowed. The A/C may be operated at OAT from -20°C (-4°F) to
+44°C (111°F). Below temperatures of -10°C (+14°F) the oil vent line must be modified by
the low temperature kit (breather line). Flight in known icing-conditions is prohibited. Smo­king is prohibited.

Section 2

Limitations

2.11 STRUCTUAL TEMPERATURE/COLOUR LIMITATION

Structure is qualified up to 72°C (161,6°F). Structure temperatures (composite) above 72°C
(161,6°F) are not permitted. Not to exceed this temperature limit, color specification for
composite structure (manufacturer document EA-03205.19) has to be complied with.

2.12 MAXIMUM OPERATING ALTITUDE

Max. certified operating altitude is 16000 ft MSL (4877 m)

2.13 TIRE PRESSURE

The tire pressure is 2800 hpa (40,2 psi).

2.14 MARKINGS AND PLACARDS

2.14.1 AIRCRAFT IDENTITY PLACARD

MANUFACTURER:
EXTRA FLUGZEUGBAU GMBH
MODEL: EA 300/S
SERIAL NUMBER: _______
TC-NUMBER:

or

FLUGZEUGPRODUKTIONS­UND VERTRIEBS-GMBH
MODEL: EA 300/S
SERIAL NUMBER: _______

EXTRA

TC-NUMBER: A67EU

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Section 2
Limitations

2.14.2 OPERATING PLACARDS

VA = 158 KTS (ACRO) (near airspeed indicator)

VA = 140 KTS (NORMAL)

THE MARKINGS AND PLACARDS INSTALLED IN (left side under canopy
THIS AIRPLANE CONTAIN OPERATING LIMITATIONS frame)
WHICH MUST BE COMPLIED WITH WHEN OPERATING
THIS AIRPLANE IN THE ACROBATIC CATEGORY.
OTHER LIMITATIONS WHICH MUST BE COMPLIED
WITH WHEN OPERATING THIS AIRPLANE IN THIS
CATEGORY OR IN THE NORMAL CATEGORY ARE
CONTAINED IN THE AIRPLANE FLIGHT MANUAL.
APPLICABLE RPM LIMITATION MUST BE OBSERVED

THIS AIRPLANE IS CERTIFICATED (on the instrument panel)
FOR VFR, DAY OPERATION.
OPERATION UNDER KNOWN ICING
CONDITIONS PROHIBITED.

Pilot´s Operating Handbook

EXTRA 300S

F U E L (near each filler cap)

AVGAS 100/100 LL

WING
TANK

120 L

OIL (on the seperate hatch

/ upper cowling)

FUEL

SELECTOR

=>

ACRO & CENTER

49 L USABLE

(12.9 US GAL)

USABLE

(31,7 US

GAL)

(on right aux. spar hardpoint)

O

F
F

NOSE DOWN <= NEUTRAL => NOSE UP (near trim lever at the right side

TRIM in the cockpit)

WING TANK (on the insrument panel under

MUST BE EMPTY FOR ACROBATICS fuel capacity indicator)

ACRO & CENTER TANK

SHOWS "ZERO" IN LEVEL FLIGHT BELOW 11.6 L (3 US GAL.)

UNUSABLE FUEL: 2 L (0.5 US GAL.)

2 - 8 Page Date: 20. April 2002

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THE REMAINING FUEL IN LEVEL FLIGHT (on the instrument panel
CANNOT BE USED SAFELY under the acro & center tank
WHEN INDICATOR READS "ZERO". fuel capacity indicator)

ACROBATIC: ± 10 G (in cockpit)
MTOW 820 KG (1808LBS)

NORMAL : + 6 G/- 3 G
MTOW 920 kg (2028 LBS)
ACROBATICS INCL. SPIN NOT APPROVED

OFF (under pump switch on the instrument panel)

BOOST PUMP

NO SMOKING (on canopy frame)

Section 2

Limitations

USE OF HEADSET IS REQUIRED (on the right side of
USE OF PARACHUTE IS RECOMMENDED instrument panel)

LOW RPM <= PROP => HIGH RPM (on RPM control unit in the

rear cockpit)

RICH <= MIXTURE => LEAN (on mixture control unit in the

rear cockpit)

CLOSE <= THROTTLE => OPEN (near throttle control in both

cockpits)

CANOPY LOCK

LOCK <= O => UNLOCK <= O => LOCK (near canopy locking handles

of each cockpit)

V E N T (near the eyeball-type adjustable vents)

O P E N

CAUTION

Particular caution must be exercised when performing (in cockpit)
maneuvers at speeds above Va (158 KIAS). Large or
abrupt control inputs above this speed may impose un­acceptably high loads which exceed the structural
capability of the aircraft.

Page Date: 20. April 2002 2 - 9

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Section 2
Limitations

Pilot´s Operating Handbook

APPROVED ACROBATIC MANEUVERS (in cockpit)
AND RECOMMENDED ENTRY AIRSPEEDS

Maneuvers speeds

min KIAS max KIAS

Segment:
horizontal Line V

s

V

ne

EXTRA 300S

45°climbing 80 V

90° up 158 V

45° diving V

90° diving V

s

s

ne

ne

V

ne

V

ne

1/4 Loop climb. 100 190

Looping 100 190

Stall turn 100 190

Aileron roll 80 158

Snap roll 80 140

"Tail-slide" 100 190

Spin V

Inverted spin V

Inverted flight > V

s

s

s

190

Less than 4 min

Knife edge >150
Less than 10 s

NO BAGGAGE (on Lexan cover aft pilot's seat, if installed)

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2.14.3 INSTRUMENT MARKINGS

AIRSPEED INDICATOR
green arc 60 Kts - 158 Kts

yellow arc 158 Kts - 220 Kts
red line 220 Kts

OIL PRESSURE INDICATOR
red line 25 Psi

yellow arc 25 Psi - 55 Psi
green arc 55 Psi - 90 Psi
yellow arc 90 Psi - 100 Psi
red line 100 Psi

OIL TEMPERATURE INDICATOR
yellow arc < 140 °F

green arc 140 °F - 210 °F
yellow arc 210 °F - 245 °F
red line 245°F

Section 2

Limitations

CYLINDERHEAD TEMPERATURE INDICATOR
yellow arc < 150 °F

green arc 150 °F - 435 °F
yellow arc 435 °F - 500 °F
red line 500°F

RPM INDICATOR
green arc 700 RPM - 2400 RPM

yellow arc 2400 RPM - 2700 RPM
red line 2700 RPM

G - METER
green arc - 5 g - + 8 g

yellow arc + 8 g - + 10 g
red line + 10 g

FUEL FLOW INDICATOR
green arc 0 gal / h - 35 gal / h

red radial 35 gal / h

Page Date: 20. April 2002 2 - 11

Section 2
Limitations

MANIFOLD PRESSURE INDICATOR
green arc 10 " Hg - 25 " Hg

yellow arc 25 " Hg - 29.5 " Hg
red radial 29.5 " Hg

2.15 KINDS OF OPERATION EQUIPMENT LIST

The aircraft may be operated in day-VFR when the appropriate equipment is installed and
operable. Flying under known icing conditions is prohibited.

The following equipment list identifies the systems and equipment upon
which type certification for each kind of operation was predicated.
The following systems and items of equipment must be installed and
operable for the particular kind of operation indicated.

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EXTRA 300S

NORMAL ACROBATIC

COMMUNICATION

1. Transceiver-VHF 1 1

ELECTRICAL POWER

1. Battery 1 1

2. Alternator 1 1

3. Ampermeter 1 1

FLIGHT CONTROL SYSTEM

1. Elevator-trim control 1 1

2. Stall warner 1 1

FUEL

1. Boost pump 1 1

2. Fuel quantity indicator 2 2

3. Manifold pressure 1 1

4. Fuel flow indicator 1 1

5. Fuel pressure 0 0

LIGHT

1. Wing-tip position / strobe light 1 1

NAVIGATION

1. Altimeter 1 1

2. Airspeed indicator 1 1

3. Mag. direction indicator 1 1

4. OAT indicator 0 0

5. Vertical speed indicator 0 0

6. Turn & bank indicator 0 0

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7. Artificial horizon 0 0

8. Directional gyro 0 0

9. Transponder

ENGINE CONTROL

1. RPM indicator 1 1

2. Exhaust gas temperature ind. 0 0

3. Cylinder head temperature ind. 0 0

OIL

1. Oil temperature indicator 1 1

2. Oil pressure indicator 1 1

FLIGHT CREW EQUIPMENT

1. Parachute 0 *

2. Seat belt 1 1

3. Headset 1 1

Section 2

Limitations

NORMAL ACROBATIC

1

11

The zeros ( 0 ) used in the above list mean that either the equipment or system, or both were
not required for type certification for that kind of operation.

Either equipment or systems in addition to those listed above may be required by the national
operating regulations.

The asterisk ( * ) used in the above list means that latest national aviation regulations must
be observed in determining whether the equipment and/or system is required.
According FAR Part 91 „General Operating and Flight Rules" each occupant of an US
registered airplane must wear an approved parachute when performing acrobatic
maneuvers.
Extra Flugzeugproduktions- und Vertriebs- GmbH considers acrobatics without wearing an
approved parachute to be unsafe.

2.16 NOISE LEVEL

The noise level with silencer Gomolzig 606000 (6 in 1) and propeller MTV-14-B-C/C190-17
has been established in accordance with ICAO Annex 16, as 77.3 dB(A)

The noise level with propeller MTV-9-B-C/C200-15 has been established in accordance with
FAR 36 Appendix G, as 73.0 dB(A).

NOTE

No determination has been made by the LBA for the FAA that the noise levels of this airplane
are or should be acceptable or unacceptable for operation at, into, or out any airport.

1

) In some airspaces Mode S Elementary Surveillance functionality is required

Page Date: 20. April 2002 2 - 13

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Section 2
Limitations

Pilot´s Operating Handbook

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Left blank intentionally

2 - 14 Page Date: 20. April 2002

Pilot´s Operating Handbook
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Emergency Procedures

Section 3

SECTION 3

EMERGENCY PROCEDURES

Table of Contents

Paragraph Page

SECTION 3 EMERGENCY PROCEDURES

3.0 INTRODUCTION................................................................................................................. 3-3

3.0.1 General ............................................................................................................................... 3-3

3.0.2 General Behaviour In Emergency Situations ....................................................................... 3-3

3.1 AIRSPEEDS FOR EMERGENCY OPERATION.................................................................. 3-4

3.2 OPERATIONAL CHECKLIST ............................................................................................. 3-4

3.2.1 Engine Failure during Take-off Roll...................................................................................... 3-4

3.2.2 Engine Failure immediately after Take-off............................................................................ 3-4

3.2.3 Engine Failure during Flight (Restart Process) .................................................................... 3-4

3.2.4 Oil System Malfunction........................................................................................................ 3-5

3.2.5 Alternator Failure................................................................................................................. 3-5

3.3 FORCED LANDINGS.......................................................................................................... 3-5

3.3.1 Emergency Landing without Engine Power ......................................................................... 3-5

3.3.2 Precautionary Landing with Engine Power........................................................................... 3-5

3.4 FIRES ................................................................................................................................. 3-6

3.4.1 During Start on Ground........................................................................................................ 3-6

3.4.2 If Engine Fails to St art ......................................................................................................... 3-6

3.4.3 Engine Fire in Flight............................................................................................................. 3-7

3.5 ICING .................................................................................................................................. 3-7

3.5.1 Inadverted Icing Encounter.................................................................................................. 3-7

3.6 UNINTENTIONAL SPIN ...................................................................................................... 3-7

3.7 MANUAL BAIL-OUT ........................................................................................................... 3-7

3.8 EMERGENCY EXIT AFTER TURN OVER.......................................................................... 3-8

3.9 ELEV A TOR CONTROL F AILURE....................................................................................... 3-8

Page Date: 20. April 2002 3 - 1

Section 3
Emergency Procedures

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3 - 2 Page Date: 20. April 2002

Pilot´s Operating Handbook
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3.0 INTRODUCTION

3.0.1 GENERAL

This section contains the checklist and procedures coping with emergencies that may
occur. This checklist must be followed in various emergencies to ensure maximum safety
for the pilot and/or aircraft.

Thorough knowledge of these procedures will enable the pilot to better cope with an
emergency. The steps should be performed in the listed sequence. However the
procedures do not restrict the pilot from taking any additional action necessary to deal with
the emergency. The procedures contain items classified as critical or noncritical. The critical
items are actions that shall be performed immediately to avoid aggravating the
emergency.

Emergency Procedures

Section 3

SECTION 3

EMERGENCY PROCEDURES

3.0.2 GENERAL BEHAVIOUR IN EMERGENCY SITUATIONS

In any emergency situation, contact should be established with a ground station as soon as
possible after completing the initial corrective action. Include position, altitude, heading,
speed, nature of the emergency and pilot's intentions in the first transmission. There after
the ground station should be kept informed of the progress of the flight and of any changes
or developments in the emergency. Three basic rules apply to most emergencies and
should be observed by each aircrew member:

1. Maintain aircraft control

2. Analyze the situation and take proper action

3. Land as soon as possible/as soon as practical

The meaning of "as soon as possible" and "as soon as practical" as used in this section is
as follows:

Land AS SOON AS POSSIBLE (ASAP) = Emergency conditions are urgent and require

an immediate landing at the nearest suitable
airfield, considering also other factors, such as
weather conditions and aircraft mass.

Land AS SOON AS PRACTICAL = Emergency conditions are less urgent and in

the aircrews judgement the flight may be
safely continued to an airfield where more
adequate facilities are available.

Page Date: 20. April 2002 3 - 3

Section 3
Emergency Procedures

3.1 AIRSPEEDS FOR EMERGENCY OPERATION

Stall speed 60 KIAS
Engine failure after take-off 80 KIAS
Best recommended gliding speed ( glide angle 1 : 6,2 )

-Normal cat. (920 kg / 2028 LBS) 90 KIAS

-Acrobatic cat. (820 kg / 1808 LBS) 80 KIAS
Precautionary landing with engine power 80 KIAS
Landing without engine power 80 KIAS
Maximum demonstrated cross wind

component 15 Knots

3.2 OPERATIONAL CHECKLIST

Pilot´s Operating Handbook

EXTRA 300S

3.2.1 ENGINE FAILURE DURING TAKE-OFF ROLL

1. Throttle IDLE

2. Brakes APPLY

3. Mixture IDLE CUT OFF

4. Ignition switch OFF

5. Master switch OFF

3.2.2 ENGINE FAILURE IMMEDIATELY AFTER TAKE-OFF

Stall speed 60 KIAS

1. Airspeed 80 KIAS

2. Mixture IDLE CUT OFF

3. Fuel shutoff valve OFF (Pull & Turn)

4. Ignition switch OFF

5. Master switch OFF

6. Forced landing PERFORM AS PRACTICABLE

3.2.3 ENGINE FAILURE DURING FLIGHT (RESTART PROCESS)

1. Airspeed 80 KIAS

2. Fuel shutoff valve CENTER TANK

3. Mixture RICH

4. Boost pump ON

5. Ignition switch BOTH
(or START if propeller has stopped)

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3.2.4 OIL SYSTEM MALFUNCTION

If oil pressure indicates low: Apply positive "g"

If oil pressure is not regained than:

1. Airspeed 80 KIAS

2. Throttle REDUCE TO IDLE

3. Engine oil temperature OBSERVE INDICATION

4. Land ASAP

If oil pressure drops to 0 psi the propeller pitch changes automatically to coarse (high) pitch
with a corresponding decrease in RPM.

3.2.5 ALTERNATOR FAILURE

An alternator failure is indicated by the red light of the low voltage monitor.
If red light illuminates:

1. Alternator SWITCH OFF AND ON

2. Low voltage monitor CHECK INDICATION

3. Red light off CONTINUE FLIGHT

W A R N I N G

WARNING

Emergency Procedures

Section 3

If red light illuminates again:

4. Land AS SOON AS PRACTICAL

3.3 FORCED LANDINGS

3.3.1 EMERGENCY LANDING WITHOUT ENGINE POWER

1. Seat belts, shoulder harnesses SECURE

2. Airspeed 80 KIAS

3. Mixture IDLE CUT OFF

4. Fuel shutoff valve OFF (Pull & Turn)

5. Ignition switch OFF

6. Master switch OFF

7. Touchdown SLIGHTLY TAIL LOW

8. Brakes OPTIMUM BRAKING

3.3.2 PRECAUTIONARY LANDING WITH ENGINE POWER

1. Seat belt, shoulder harness SECURE

2. Airspeed 80 KIAS

3. Selected field FLY OVER,

4. Master switch OFF

5. Touchdown SLIGHTLY TAIL LOW

6. Ignition switch OFF

7. Mixture IDLE CUT OFF

8. Fuel shutoff valve OFF (Pull & Turn)

9. Brakes APPLY HEAVILY

noting terrain and
obstructions, then
reaching a safe
altitude and airspeed

Page Date: 20. April 2002 3 - 5

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Section 3
Emergency Procedures

3.4 FIRES

3.4.1 DURING START ON GROUND

1. Cranking CONTINUE to get a start

2. Fuel shutoff valve OFF (Pull & Turn)

3. Power 1700 RPM for one minute.

4. Engine SHUT DOWN

5. After engine stop ABANDON aircraft and

Pilot´s Operating Handbook

EXTRA 300S

which would suck the
flames and accumulated
fuel through the air
inlet and into the engine.

inspect for damage

6. Fire EXTINGUISH using fire

Do not open engine compartment access doors
while engine is on fire!

3.4.2 IF ENGINE FAILS TO START

1. Cranking CONTINUE

2. Throttle FULL OPEN

3. Mixture IDLE CUT OFF

4. Fuel shutoff valve OFF (Pull & Turn)

If fire is extinguished

5. Master switch OFF

6. Ignition switch OFF

7. Engine compartment INSPECT

WARNING

W A R N I N G

extinguisher if available

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3.4.3 ENGINE FIRE IN FLIGHT

1. Mixture IDLE CUT OFF

2. Fuel shutoff valve OFF (Pull & Turn)

3. Master switch OFF

4. Airspeed 100 KIAS, find your

5. Land as soon as possible

3.5 ICING

3.5.1 INADVERTED ICING ENCOUNTER

1. Turn back or change altitude to obtain an outside temperature that is less
conductive to icing.

2. Plan a landing at the nearest airfield. With extremely rapid ice build-up select a
suitable "off airport" landing field.

Emergency Procedures

Section 3

airspeed/attitude
which will keep the
fire away from the cockpit

3.6 UNINTENTIONAL SPIN

Refer to section 4 (Normal Procedures) acrobatic maneuver, spin recovery

3.7 MANUAL BAIL-OUT

When in an emergency situation that requires abandoning the aircraft and while wearing a
parachute, which is at least strongly recommended for acrobatics:

- Reduce speed to 100 Kts if possible

- Pull mixture to lean

- Open canopy (the low pressure over the canopy in normal flight
will flip the canopy fully open immediately)

- Take off headset

- Open seat belt

- Leave airplane to the left side

- Try to avoid wing and tail

- Open parachute

Page Date: 31. January 2006

Page Date: 20. April 2002 3 - 7

Section 3
Emergency Procedures

3.8 EMERGENCY EXIT AFTER TURN OVER

1. Master switch OFF

2. Fuel shutoff valve OFF (Pull & Turn)

3. Seat belts OPEN

4. Parachute harnesses OPEN

5. Canopy handle PULL TO OPEN

W A R N I N G

WARNING

If canopy fails to open break the canopy.

6. Aircraft EVACUATE ASAP

3.9 ELEVATOR CONTROL FAILURE

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EXTRA 300S

In case of elevator control failure the aircraft can be flown with the elevator trim.
In this case trim nose up to the desired speed and control horizontal flight or descend with
engine power.
For landing trim nose up and establish a shallow descend by adjusting throttle. To flair the
plane gently increase power to bring the nose up to landing attitude.

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Normal Procedures

Section 4

SECTION 4

NORMAL PROCEDURES

Table of Contents

Paragraph Page

SECTION 4 NORMAL PROCEDURES

4.0 GENERAL ........................................................................................................................... 4-3

4.0.1 Airspeeds for Normal Operation .......................................................................................... 4-3

4.0.2 Checklist and Procedures ................................................................................................... 4-3

4.1 PREFLIGHT INSPECTION ................................................................................................. 4-4

4.1.1 Exterior Inspection Illustration.............................................................................................. 4-4

4.1.2 General ............................................................................................................................... 4-4

4.3 STARTING PROCEDURES ................................................................................................ 4-6

4.3.1 Cold Engines....................................................................................................................... 4-6

4.3.2 Hot Engines......................................................................................................................... 4-6

4.4 TAXIING THE AIRCRAFT ................................................................................................... 4-6

4.5 TAKE-OFF PROCEDURE................................................................................................... 4-7

4.5.1 Before Take-off.................................................................................................................... 4-7

4.5.2 Take-off ............................................................................................................................... 4-7

4.6 CLIMB................................................................................................................................. 4-7

4.7 CRUISE............................................................................................................................... 4-7

4.8 LANDING PROCEDURES .................................................................................................. 4-8

4.8.1 Descent ............................................................................................................................... 4-8

4.8.2 Approach............................................................................................................................. 4-8

4.8.3 Before Landing.................................................................................................................... 4-8

4.8.4 Normal Landing................................................................................................................... 4-8

4.9 GO-AROUND...................................................................................................................... 4-9

4.10 SHUTDOWN ....................................................................................................................... 4-9

4.11 LEAVING THE AIRCRAFT.................................................................................................. 4-9

4.12 ACROBATIC MANEUVERS.............................................................................................. 4-10

4.12.1 General ............................................................................................................................. 4-10

4.12.2 Maneuvers ........................................................................................................................4-10

4.12.3 Spin ................................................................................................................................... 4-12

Page Date: 20. April 2002 4 - 1

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Section 4
Normal Procedures

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SECTION 4

NORMAL PROCEDURE

4.0 GENERAL

4.0.1 AIRSPEEDS FOR NORMAL OPERATION

CATEGORY ACRO NORMAL
Start:

-Rotating Speed 60 6 5

Climb:

Normal Procedures

Section 4

SPEEDS IN KIAS

-Vx 87 93

-Vy 96 104

-Recommended Normal

Climb Speed 100 110
Max. Cruise Speed 185 185
Landing:

-Approach 75 80

-On Final 65 70

-Go-Around Speed 90 100

Recommended Airspeed
For Flight In Rough Air (maximum) VA= 158 VA= 140

Max. Demonstrated Cross
Wind Component 15 Kts 15 Kts

4.0.2 CHECKLIST AND PROCEDURES

This handbook contains the checklist and procedures to operate the aircraft in normal and
acrobatic operation. The pilot should be familiar with all procedures contained in this Pilot's
Operating Handbook, which should be carried on board. The pilot has to comply with
Checklist for daily check and inspections (see Section 8, Handling, Servicing and
Maintenance).

Page Date: 20. April 2002 4 - 3

Section 4
Normal Procedures

4.1 PREFLIGHT INSPECTION

4.1.1 EXTERIOR INSPECTION ILLUSTRATION

4.1.2 GENERAL

Visually check airplane for general condition during walk around inspection.
Perform exterior check as outlined in the picture above in counterclockwise direction.

Pilot´s Operating Handbook

EXTRA 300S

3

4

2

1

5

4.2 CHECKLIST PROCEDURES

1) Cockpit

1. Pilot's Operating Handbook (AVAILABLE)

2. Airplane weight and balance CHECKED

3. Ignition switch OFF

4. Master switch ON

5. Fuel quantity indicators CHECK

6. Master switch OFF

7. Fuel selector * ACRO & CENTER TANK

Although safe operation did not require the use of the tanks in a specific sequence, it is
recommended to set fuel selector to "ACRO & CENTER TANK" position!

2) Empennage

1. All round inspection, canopy, surfaces,
stabilizer, elevator, trim rudder and tailwheel CHECK

2. Horizontal stabilizer attachment bols CHECK FOR FREEPLAY BY

3) Right Wing

NOTE *

*Note:

MOVING THE TIP OF THE
HORIZ. STABILIZER UP- AND
DOWNWARDS

1. Aileron, freedom of movement and security CHECK

2. Trailing edge CHECK

3. Fuel tank vent opening (right landing gear) CHECK

4. Fuel quantity CHECK

5. Fuel tank filler cap CHECK

6. Right landing gear, wheel and brake CHECK

7. Stall warning vane CHECK

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4) Nose

1. Engine oil dipstick CHECK

2. Propeller and spinner CHECK

3. Air inlet CHECK

4. Acro & center fuel tank drain DRAIN FOR AT LEAST 4

5. Wing fuel tank drain DRAIN FOR AT LEAST 4

6. Fuel filter drain DRAIN FOR AT LEAST 4

7. Exhaust silencer (if installed) CHECK FOR DAMAGE AND

Normal Procedures

Section 4

SECONDS TO CLEAR SUMP OF
POSSIBLE WATER;
CHECK CLOSED

SECONDS TO CLEAR SUMP OF
POSSIBLE WATER;
CHECK CLOSED

SECONDS TO CLEAR
FILTER OF POSSIBLE WATER;
CHECK CLOSED

SECURE ATTACHMENT

5) Left wing

1. Left landing gear, wheel and brakes CHECK

2. Fuel quantity CHECK

3. Fuel tank filler cap CHECK

4. Pitot cover REMOVE

5. Trailing edge CHECK

6. Aileron, freedom of movement and security CHECK

6) Before starting engine

1. Preflight inspection COMPLETE

2. Parachute handling briefing COMPLETE

3. Seat, seatbelts, shoulder harnesses ADJUST AND LOCK

4. Canopy CLOSE AND LOCK

CAUTION:

CAUTION

Handles of the canopy lock mechanism must be in the most opposite position indicated with
a red line on the canopy frame. Check gap between canopy frame and fuselage fairing!

5. Brake CHECK

6. Master switch ON

7. Avionics power switch OFF

8. Electrical equipment OFF

9. Alternator ON

10.Wingtip position / Strobe lights ON

Page Date: 20. April 2002 4 - 5

Section 4
Normal Procedures

4.3 STARTING PROCEDURES

4.3.1 COLD ENGINES

The following starting procedures are recommended, however, the
starting conditions may necessitate some variation from
these procedures.

1. Perform pre-flight inspection.

2. Set propeller governor control in "High RPM" position.

3. Open throttle approximately 1/4 travel.

4. Turn boost pump "ON".

5. Move mixture control to "FULL RICH" until a slight but steady
fuel flow is noted (approximately 3 to 5 seconds) and return
mixture control to "IDLE CUT-OFF".
Turn bost pump "OFF".

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6. Engage starter.

7. When engine fires release the ignition switch back to "BOTH".

8. Move mixture control slowly and smoothly to "FULL RICH".

9. Check the oil pressure gauge. If minimum oil pressure is not
indicated within 30 seconds, shut off the engine and determine trouble.

4.3.2 HOT ENGINES

Because of the fact that the fuel percolates and the system must be cleared of vapor, it is
recommended to use the same procedure as outlined for cold engine start.

4.4 TAXIING THE AIRCRAFT

1. Canopy CLOSE AND LOCK

2. Brake CHECK

3. Altimeter Set on QFE or QNH

4. Avionic master switch ON

5. Electrical equipment ON

6. Radio Set and test

7. Mixture Leave in "FULL RICH" position

Scale error max. +60 ft

Operate only with the propeller in minimum blade angle (High RPM).
Warm-up at approximately 1000-1200 RPM. The engine is ready for take-off when the
throttle can be opened without the engine faltering.

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4.5 TAKE-OFF PROCEDURE

4.5.1 BEFORE TAKE-OFF

Before you line up at the runway for take-off:

- Check oil pressure and oil temperature.

- Check the magnetos on 1800 RPM. Allowed drop is 175 RPM
(max. difference 50 RPM).

- Check Alternator Output

- Move also the propeller control through its complete range to check operation and
return to full "High RPM" position. Turn boost pump "ON" (check indicator movement on
the fuel flow gauche).

The RPM Gauge is electronically operated. To check the magnetos the RPM source switch
must be set to the same magento as the igintion switch. Otherwise the gauge will show
zero.

Normal Procedures

Section 4

NOTE

4.5.2 TAKE-OFF

Set throttle smoothly to max and let the airspeed go up to 60-65 KIAS. A light pressure on
the stick lifts the tail to horizontal position. Rotate the aircraft at 65 KIAS. On reaching climb
speed of 100 KIAS reduce the RPM / Manifold Pressure to 2400/24" and proceed climbing.

4.6 CLIMB

Due to noise protection, the maximum continous RPM is restricted to 2400.
If not stated somewhere else (refer to Section: 4.12 Acrobatic Maneuvers) the aircraft may

be operated in the acrobatic maneuvers up to 2700 RPM. RPM above 2400 should,
however, be used only for acrobatic maneuvers when necessary for maximum performance
in order to avoid unnecessary noise.

Turn boost pump "OFF".

4.7 CRUISE

1. Altitude - As selected

2. Throttle/RPM - Adjust for cruising speed

3. Mixture - Adjust for minimum fuel consumption

4. Trim - As required

5. Fuel - Check periodically

Page Date: 20. April 2002 4 - 7

Section 4
Normal Procedures

4.8 LANDING PROCEDURES

4.8.1 DESCENT

1. Throttle - Reduce

2. Mixture - "FULL RICH"

3. RPM Control - Set to 2400 RPM

4. Trim - Adjust

5. Fuel selector* - "ACRO & CENTER TANK"

Although safe operation did not require the use of the tanks in a specific sequence, it is
recommended to set fuel selector to "ACRO & CENTER TANK" position!

4.8.2 APPROACH

1. Boost pump - ON

2. Mixture - set to "Rich"

3. Airspeed - reduce to approach speed

4. Propeller pitch - set to low angle (High RPM).

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NOTE *

It is recommended to set the RPM to 2400 during approach and landing
in order to avoid unnecessary noise.
In case of "Go Around", RPM control must be set to max. RPM before
applying power.

4.8.3 BEFORE LANDING

1. Landing approach - proceed at 80 KIAS

2. Airspeed on final - maintain 70 KIAS

3. Elevator trim - adjust

Stall speed will be
MTOW = 820 kg : 55 KIAS

MTOW = 920 kg : 59 KIAS

N O T E

NOTE

NOTE

N O T E

4.8.4 NORMAL LANDING

1. Landing - perform as practicable
with respect to surface
and weather condition

2. Touchdown - 3 point landing

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3. Throttle - CLOSE / IDLE

4. Braking - Minimum required

4.9 GO-AROUND

Decide early in the approach if it is necessary to go around and
then start go-around before too low altitude and airspeed are
reached.

Proceed as follows:

1. RPM control - "HIGH RPM" / Full forward

2. Throttle - "OPEN" / Take-off power

3. Airspeed - Minimum 90 KIAS

N O T E

NOTE

The rudder is effective down to 30 KIAS

rotate to go-around altitude

Normal Procedures

Section 4

4.10 SHUTDOWN

1. Boost pump - "OFF"

2. Engine - Run for 1 min. at 1000 RPM

3. Dead cut check - Perform

4. Avionic master switch - "OFF" (if installed)

5. Mixture - "IDLE CUT OFF"

6. Ignition switch - "OFF"

7. Master switch - "OFF"

4.11 LEAVING THE AIRCRAFT

1. Canopy - Close and lock

2. Aircraft - Secure

3. Pitot cover - Attach

4. Log book - Complete

Page Date: 20. April 2002 4 - 9

Section 4
Normal Procedures

4.12 ACROBATIC MANEUVERS

4.12.1 GENERAL

Prior to executing these maneuvers tighten harnesses and check all loose items are
stowed. Start the maneuvers at safe altitude and max continuous power setting if not
otherwise noted.

For maneuver limits refer to Section 2 LIMITATIONS.
After termination of acrobatic maneuvers the artificial horizon (if installed) must be reset if

possible.
At high negative g-loads and zero g-periods it is normal that oil pressure and RPM

indication might drop down momentarily returning to normal status at positive g-loads.

N O T E

NOTE

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The high permissible load factors of the airplane may exceed the individual physiological
limits of pilot . This fact must be considered when pulling or pushing high g's.

4.12.2 MANEUVERS

Particular caution must be exercised when performing maneuvers at speeds above
Va (158 KIAS). Large or abrupt control inputs above this speed may impose
unacceptably high loads which exceed the structural capability of the aircraft.

Acrobatics is traditionally understood as maneuvers like loop, humpty bump, hammerhead
turn, aileron roll etc..

This manual does not undertake to teach acrobatics, however, it is meant to demonstrate
the plane's capabilities.

For this reason maneuvers are divided into segments. The segments are described.
Limitations are pointed out.

WARNING

CAUTION

CAUTION

- Segment horizontal line:

A horizontal line may be flown with any speed between Vs and V

4 - 10 Page Date: 20. April 2002

ne

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- Segment line 45° climbing:
The plane will follow the line at max. power. The speed will not decrease below 80 KIAS.

- Segment line 90° up:
Any entry speed may be used. Out of a horizontal pull-up at 200 KIAS the vertical
penetration will be 2.500 ft. The speed will gradually decrease to 0.

In extremely long lines an RPM decay may occur. This is related to a loss of oil pressure.
Positive g´s should be pulled immediately in order to protect the engine. Oil pressure will
return immediately.

- Segment line 45° diving:
Throttle must be reduced in order to avoid exceeding Vne.

N O T E

NOTE

Normal Procedures

Section 4

- Segment lin 90° diving:
Throttle must be reduced to idle in order to avoid exceeding Vne.

Above segments may be filled up with aileron rolls on snap rolls. Watch VA = 158 KIAS for
aileron rolls with max. deflection.
Snap rolls should not be performed at speeds above 140 KIAS.

- Segment 1/4 loop, climbing:
The minimum recommended speed is 100 KIAS. If the maneuver is to be followed by a
vertical line, a higher entry speed is required depending on the expected length of the
line. A complete loop can be performed at speeds above 100 KIAS.

NOTE

Since the maximum horizontal speed is 185 KIAS, higher speeds should be avoided in
acrobatics since an unnecessary loss of altitude would occur.

- Torque maneuvers:
All maneuvers with high angular velocity associated with high propeller RPM must be
considered dangerous for the engine crankshaft.

Although wooden composite propeller blades are used, the gyroscopic forces at the prop
flange are extremely high.

CAUTION

If performing a gyroscopic maneuver such as flat spin, power on, or knife edge spin, reduce
RPM to 2400 in order to minimize the gyroscopic forces.

Page Date: 20. April 2002 4 - 11

Section 4
Normal Procedures

4.12.3 SPIN

Pilot´s Operating Handbook

EXTRA 300S

To enter a spin proceed as follows:

- Reduce speed, power idle

- When the plane stalls:

- kick rudder to desired spin direction

- hold ailerons neutral

- stick back (positive spinning), Stick forward (negative spinning)

The plane will immediately enter a stable spin.

- Ailerons against spin direction will make the spin flatter.

- Ailerons into spin direction will lead to a spiral dive.
Above apply for positive and negative spinning.

To stop the spin:

- Apply opposite rudder

- Make sure, power idle

- Hold ailerons neutral

- Stick to neutral position
The plane will recover within 1/2 turn.

Recovery can still be improved by feeding in in-spin ailerons.

N O T E

NOTE

If ever disorientation should occur during spins (normal or inverted) one method always
works to stop the spin:

- Power idle

- Kick rudder to the heavier side
(this will always be against spin direction)

- Take hands off the stick
The spin will end after 1/2 turn. The plane will be in a steep dive in a side-slip.

Recovery to normal flight can be performed easily.

N O T E

NOTE

After six turns of spinning the altitude loss including recovery is 2000 ft.

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Section 5

Performance

SECTION 5

PERFORMANCE

Table of Contents

Paragraph Page

SECTION 5 PERFORMANCE

5.1 GENERAL ........................................................................................................................... 5-3

5.1.1 Performance Charts ............................................................................................................ 5-3

5.1.2 Definitions of Terms............................................................................................................. 5-3

5.1.3 Sample Problem.................................................................................................................. 5-3

5.2 ISA CONVERSION.............................................................................................................. 5-5

5.3 AIRSPEED CALIBRA TION ................................................................................................. 5-6

5.4 STALL SPEED .................................................................................................................... 5-7

5.5 TAKE-OFF PERFORMANCE.............................................................................................. 5-8

5.6 RA TE OF CLIMB PERFORMANCE.................................................................................... 5-9

5.7 TIME TO CLIMB, FUEL TO CLIMB .................................................................................. 5-10

5.8 RANGE AND ENDURANCE ............................................................................................. 5-11

5.9 FUEL CONSUMPTION ..................................................................................................... 5-12

5.10 CRUISE PERFORMANCE ................................................................................................ 5-13

5.11 LANDING PERFORMANCE ............................................................................................. 5-14

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Performance

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5.1 GENERAL

Performance data charts on the following pages are presented to facilitate the planning of
flights in detail and with reasonable accuracy under various conditions. The data in the
charts have been computed from actual flight tests with the aircraft and engine in good
condition and using average piloting techniques.

It should be noted that the performance information presented in the range and endurance
charts allow for 45 minutes reserve fuel at specified speeds. Some indeterminate variables
such as engine and propeller, air turbulence and others may account for variations as high
as 10% or more in range and endurance. Therefore, it is important to utilize all available
information to estimate the fuel required for the particular flight.

5.1.1 Performance Charts

Section 5

Performance

SECTION 5

PERFORMANCE

Performance data are presented in tabular or graphical form to illustrate the effect of diffe­rent variables. Sufficiently detailed information are provided in the tables so that
conservative values can be selected and used to determine the particular performance
figure with reasonable accuracy.

All speeds in this chapter are Indicated Air Speeds (IAS). The performance figures below
are given under following conditions.

1. Maximum allowed weight 920 kg (2028 lbs) except otherwise stated

2. Take-off and landing on concrete surface.

3. No wind.

4. Standard atmospheric condition.

5.1.2 Definitions of Terms

For definition of terms, abbreviations and symbols refer to section 1, General.

5.1.3 Sample Problem

TAKE-OFF CONDITIONS

Field Pressure Alt 2000 ft
Temperature 15°C
Wind Component (Headwind) 8 KT
Field Length 3000 ft

CRUISE CONDITIONS

Total Distance 400 NM
Pressure Altitude 8000 ft
Temperature (ISA) -1°C

Page Date: 20. April 2002 5 - 3

Section 5
Performance

Pilot´s Operating Handbook

EXTRA 300S

TAKE-OFF

Take-Off Distance is shown by Fig. 5.5
Example:

-T/O Weight: 870 kg (1918 lbs)

-Ground Roll: 112 m (367 ft)

-Total Distance to clear a 50 ft obstacle: 248 m (813 ft)

These distances are well within the available field length incl. the 8 Kt headwind.

RATE OF CLIMB

Fig. 5.6 shows the Rate Of Climb using Takeoff Power
The Rate of Climb at 2000 ft : 2320 ft/min
The Time to Climb from 2000 ft to 8000 ft is acc. to Fig. 5.7:

=> (4,0 - 0,9) min = 3,1 min

The Fuel to Climb from 2000 ft to 8000 ft is:

=> (5,8 - 1,4) Liters = 4,4 Liters (1.2 US Gal.)

CRUISE

Cruise Altitude and Power Setting should be determined for most economical fuel
consumption and several other considerations. In an altitude of 8000 ft and a Power Setting
of 65 % a Fuel Consumption of 52 L/H (13.7 US Gal/H) and 3,25 NM/L (12.3 NM/US Gal)
can be obtained by Fig. 5.9.

RANGE AND ENDURANCE

Fig. 5.8 presents Range and Endurance values for a T/O Weight of 920 kg (2028 lbs)
including fuel for warm up and Take-Off from SL, max continuous Power climb to cruising
altitude, and a reserve of 21 liter (5.5 US Gal.) for 45 minutes with 45% Power. 2 liters (0.53
US Gal.) unusable fuel is taken into account.

For the sample problem (appr.)

Total Fuel 171 L (45.17 US Gal.)
Warm Up & T/O- 5 L (1.32 US Gal.)
Reserve - 21 L (5.55 US Gal.)
Unusable Fuel - 2 L (0.53 US Gal.)

====== ============

Usable Fuel 143 L (37.8 US Gal.)
Range 415 NM (768 km)

Endurance 2.49 HRS

5 - 4 Page Date: 20. April 2002

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5.2 ISA CONVERSION

ISA Conversion of pressure altitude and outside air temperatur

Section 5

Performance

Page Date: 20. April 2002 5 - 5

Section 5
Performance

5.3 AIRSPEED CALIBRATION

Pilot´s Operating Handbook

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NOTE

Indicated airspeed assumes zero instrument error

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5.4 STALL SPEED

CONDITION:
POWER IDLE

FORWARD C/G STALL SPEEDS

WEIGHT CATEGORY 0° 30° 45°

920 kg NORMAL KIAS KIAS KIAS
(2028 lbs) 59 64 70

820 kg ACRO KIAS KIAS KIAS
(1808 lbs) 55 59 65

Section 5

Performance

ANGLE OF BANK

1g 1,15 g 1,41 g

Max altitude loss during stall recovery is approximately 100 ft

Page Date: 20. April 2002 5 - 7

Section 5
Performance

5.5 TAKE-OFF PERFORMANCE

Power : T/O Power
Runway: Concrete

Note :
For every 5 kts headwind, the T/O distance can be decreased by 4%. For every 3 kts

Tailwind (up to 10) kts, the T/O distance is increased by 10%. On a solid, dry and plain
Grass Runway, the T/O is increased by 15%.

OAT 0°C (32°F) 15°C (59°F) 30°C (86°F)

Pilot´s Operating Handbook

EXTRA 300S

T/O Rotat- PA T/O T/O T/O T/O T/O T/O

weight ing Roll over Roll over Roll over

Speed 50 ft 50 ft 50 ft

kg (lbs) KIAS ft m (ft) m (ft) m (ft) m (ft) m (ft) m (ft)

920 65 SL 96 (315) 207 (679) 115 (377) 248 (813) 133 (436) 285 (935)

(2028) 2000 115 (377) 248 (814) 138 (453) 298 (978) 160 (525) 342 (1122)

4000 138 (453) 298 (978) 166 (545) 357 (1171) 192 (630) 410 (1345)
6000 166 (545) 358 (1175) 199 (653) 429 (1407) 230 (755) 492 (1614)

870 62 SL 78 (256) 167 (548) 93 (305) 200 (656) 107 (351) 230 (755)

(1918) 2000 94 (308) 200 (656) 112 (367) 240 (787) 128 (420) 276 (906)

4000 112 (367) 241 (791) 134 (440) 288 (945) 154 (505) 331 (1086)
6000 135 (443) 289 (948) 161 (528) 346 (1135) 185 (607) 397 (1302)

820 60 SL 67 (220) 114 (374) 79 (259) 170 (558) 93 (305) 200 (656)

(1808) 2000 80 (262) 173 (568) 95 (312) 204 (669) 112 (367) 240 (787)

4000 97 (318) 207 (679) 114 (374) 248 (814) 134 (440) 288 (945)
6000 116 (381) 249 (817) 137 (449) 294 (965) 161 (528) 347 (1138)

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5.6 RATE OF CLIMB PERFORMANCE

Section 5

Performance

(lbs)

RED LINE

EXAMPLE: WEIGHT 850 KG (1874 LBS)

PA: 2000 ft (ISA) 8000 ft (ISA)

ROC: 2320 ft/min 1520 ft/min

(86°F)

(68°F)

2095 1985 1874 1764 1654

(50°F)

(32°F)

(14°F)

(-4°F)

-36F -18F +18F +36F

Page Date: 20. April 2002 5 - 9

Section 5
Performance

5.7 TIME TO CLIMB, FUEL TO CLIMB

Pilot´s Operating Handbook

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LTR

(US GAL.)

EXAMPLE

WEIGHT: 850 KG (1874 LBS)

ALT: 2000 ft (ISA) => 8000 ft (ISA)

TIME TO CLIMB: 3.1 min

FUEL TO CLIMB: 4.4 ltr (1.16 US Gal.)

2029 lbs

1874 lbs

1654 lbs

FUEL TO CLIMB

0 .53 1.59 2.64 3.70 4.76 5.81

WEIGHT / KG

(LBS)

CONDITIONS:

MAX. CONT. POWER CLIMB

AT VY SPEED; ISA

5 - 10 Page Date: 20. April 2002

1544 1654 1764 1874 1985 2095

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5.8 RANGE AND ENDURANCE

RESERVE: 21 LTR (5.5 US GAL.)

UNUSABLE FUEL: 2 LTR (0.5 US GAL.)

Section 5

Performance

T/O WEIGHT: 920 KG (2028 LBS)

TOTAL FUEL CAP.: 171 LTR (45.2 US GAL.)

CONDITION:

INCL. WARM UP & T/O: 5 LTR (1.3 US GAL.)

T/O FROM SL AND MAX CONT. POWER CLIMB

TO CRUISING ALTITUDE

(ISA CONDITIONS)

Page Date: 20. April 2002 5 - 11

Section 5
Performance

5.9 FUEL CONSUMPTION

(23.8)
(21.1)
(18.5)
(15.9)
(13.2)
(10.6)
(7.9)
(5.3)

Pilot´s Operating Handbook

EXTRA 300S

(2.6)
GAL

HOUR

(15.1)
(13.2)
(11.4)
(9.5)
(7.6)
(5.7)

EXAMPLE:
PA = 8000 ft (ISA); POWER SETTING 65%
FUEL CONSUMPTION:
=> 52 LTR/HRS (13.7 GAL/HRS)
=> 3.25 NM/LTR (12.3 NM/GAL)

(3.8)
(1.9)

NM
GAL

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5.10 CRUISE PERFORMANCE

Range and Endurance values for a T/O Weight of 920 kg (2028 lbs) including fuel for warm­up and Take-Off from SL, max. cont. Power climb to cruising altitude, and a reserve of 21
liters (5.55 Gal) for 45 minutes with 45% Power. 2 liters (0.53 Gal) unusable fuel is taken
into account. (At ISA - Conditions.)

Section 5

Performance

PA Eng. Manif. Power Setting Fuel TAS IAS Endur. Range Mixture

[ft] [RPM] [IN HG] [%] [Hp] [l/h] [gal/h] [Kts] [Kts] [h] [NM] Best ...

2000 2400 25,1 75 225 68,7 (18,2) 167,6 160 1.91 320 Power

2200 24,2 65 195 50,5 (13,3) 159,3 152 2.60 413 Economy
2000 23,5 55 165 42,6 (11.3) 150,2 144 3.08 462 Economy
2000 20,2 45 135 36,5 (9,6) 139,9 134 3.59 502 Economy

4000 2400 24,6 75 225 68,7 (18,2) 170,9 158 1.91 324 Power

2200 23,7 65 195 50,5 (13,3) 162,4 150 2.59 418 Economy
2000 23,0 55 165 42,6 (11,3) 153,1 142 3.06 467 Economy
2000 19,7 45 135 36,5 (9,6) 142,6 133 3.59 507 Economy

6000 2200 23,2 65 195 50,5 (13,3) 165,6 149 2.57 422 Economy

2000 22,5 55 165 42,6 (11.3) 156,1 141 3.04 472 Economy
2000 19,3 45 135 36,5 (9,6) 145,4 131 3.53 512 Economy

8000 2350 21,5 65 195 52,0 (13,7) 169,0 147 2.49 415 Economy

2050 21,4 55 165 43,0 (11,4) 159,3 139 2.99 472 Economy
2000 18,8 45 135 36,5 (9,6) 148,4 130 3.51 517 Economy

10000 2150 19,9 55 165 43,7 (11,5) 162,5 138 2.93 469 Economy

2000 18,4 45 135 36,5 (9,6) 151,4 129 3.48 522 Economy

12000 2300 18,3 55 165 45,2 (11,9) 165,9 136 2.81 458 Economy

2000 17,9 45 135 36,5 (9,6) 154,5 127 3.44 526 Economy

14000 2400 17,0 55 165 46,7 (12,3) 169,4 135 2.71 446 Economy

2075 17,7 45 135 37,1 (9,8) 157,8 122 3.36 520 Economy

Press. Consumption 1 1 2

NOTE

1 For temperatures above/ below Standard (ISA), increase/decrease Range 1,7% and

Endurance 1,1% for each 10°C above/below Standard Day Temperature for particular
altitude.

2 "Best Power" or "Best Economy" see latest issue of Textron Lycoming Operator`s

Manual (4-10) Series AEIO 540.

Page Date: 20. April 2002 5 - 13

Section 5
Performance

Pilot´s Operating Handbook

EXTRA 300S

5.11 LANDING PERFORMANCE Power : Idle

Runway: Concrete
Brakes: maximum

NOTE

For every knot headwind, the landing distance can be decreased by 3%.
On a solid, dry and plain Grass Runway, the landing is increased by 15%.

OAT 0°C (32°F) 15°C (59°F) 30°C (86°F)

Landing Airspeed PA Land. Land. Land. Land. Land. Land.

weight Roll over Roll over Roll over

50 ft 50 ft 50 ft

[kg] / [KIAS] [ft] [m] / (ft) [m] /(ft) [m] / (ft) [m] / (ft) [m] / (ft) [m] / (ft)

(lbs)

920 80 SL 171 (561) 527 (1729) 177 (581) 548 (1798) 185 (607) 586 (1923)

(2028) 2000 181 (594) 558 (1831) 188 (617) 580 (1903) 197 (646) 602 (1975)

4000 192 (630) 592 (1942) 199 (653) 615 (2018) 208 (682) 639 (2096)
6000 203 (666) 627 (2057) 211 (692) 652 (2139) 220 (722) 678 (2224)

870 78 SL 158 (518) 488 (1601) 164 (538) 507 (1663) 171 (561) 527 (1729)

(1918) 2000 165 (541) 518 (1699) 175 (574) 537 (1762) 181 (594) 558 (1831)

4000 177 (581) 548 (1798) 185 (607) 570 (1870) 192 (630) 592 (1942)
6000 188 (617) 582 (1909) 195 (640) 605 (1985) 203 (666) 627 (2057)

820 75 SL 150 (492) 465 (1526) 156 (512) 483 (1585) 163 (535) 502 (1647)

(1809) 2000 159 (522) 492 (1614) 166 (545) 511 (1677) 173 (568) 532 (1745)

4000 168 (551) 522 (1713) 176 (577) 543 (1781) 184 (604) 565 (1854)
6000 179 (587) 553 (1814) 186 (610) 575 (1886) 194 (636) 598 (1962)

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Weight and Balance and Equipment List

Section 6

SECTION 6

WEIGHT AND BALANCE AND EQUIPMENT LIST

Table of Contents

Paragraph Page

SECTION 6 WEIGHT AND BALANCE AND EQUIPMENT LIST

6.1 GENERAL ........................................................................................................................... 6-3

6.2 AIRCRAFT WEIGHING PROCEDURE ............................................................................... 6-3

6.2.1 Owners Weight and Balance Record................................................................................... 6-4

6.3 CENTER OF GRA VITY CALCULATION (SAMPLE PROBLEM) ........................................ 6-5

6.3.1 Sample................................................................................................................................ 6-7

6.3.2 Weight and Balance Record Sheet...................................................................................... 6-7

6.4 LOADING WEIGHTS AND MOMENTS .............................................................................. 6-8

6.5 WEIGHTS AND MOMENT LIMITS ..................................................................................... 6-9

6.6 EQUIPMENT LIST ............................................................................................................ 6-10

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Section 6
Weight and Balance and Equipment List

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6.1 GENERAL

This section describes the procedure for establishing the basic weight and moment of the
aircraft. Sample forms are provided for reference. Procedures for calculating the weight and
movement for various operations are also provided. A comprehensive list of all equipment
available for this aircraft is included. It is the responsibility of the pilot to ensure that the
aircraft is loaded properly.

6.2 AIRCRAFT WEIGHING PROCEDURE

The aircraft weight is determined by weighing all three wheel
loads simultaneously by three scales with the aircraft levelled.
(Upper fuselage reference line horizontal)

Datum line for weight arms x is the fire wall.
X1 = distance: fire wall - main wheel
X2 = distance: fire wall - tail wheel

Weight and Balance and Equipment List

Section 6

XN = distance: fire wall - item N
XG = distance: fire wall - Center of Gravity
W1 = Sum of weights indicated by the two scales below the main wheels
W2 = Weight indicated by the scale below the tail wheel
W = Total weight = W1 + W2
XG = (W1 x X1) + (W2 x X2) = C/G position

W

Reference Firewall (plane)

x

G

x

2

x

W2

W

1

W1

(W1 x X1) + (W2 x X2)

W = W1 + W2 ,

Page Date: 20. April 2002 6 - 3

Page Date: 31. January 2006

XG =

W

Section 6
Weight and Balance and Equipment List

If a new weight is added to the known old weight and C/G position the resulting new weight
and C/G can be obtained by a simple calculation.

Situation before adding item:
Wo, Xo = Airplane weight, C/G position

Wn, Xn = Weight, distance from fire wall of item to add
New Weight of airplane and new C/G:
W = Wo + Wn
XG = Wo x Xo + Wn x Xn : C/G position

W

6.2.1 Owners Weight and Balance Record

Pilot´s Operating Handbook

EXTRA 300S

Enter below all weight change data from aircraft log book.

EXTRA 300/S SERIAL NUMBER: 031 REGISTRATION: D - E J X A
Date Description of Weight change Running empty

modification Added (+), Removed (-) weight

Wt./kg Arm/cm Moment/kg*cm Wt./kg Moment/kg*cm

[lbs] [inch] [lbs*inch] [lbs] [lbs*inch]

06.09.91 Empty weight ___ ___ _______ 671 45067
as delivered

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6.3 CENTER OF GRAVITY CALCULATION (SAMPLE PROBLEM)

PILOT FUEL IN FUEL IN FUEL IN

ACRO TANK CENTER TANK WING TANK

Position 9 LTR 42 LTR 120 LTR

(2,37 US GAL) (11,1 US GAL) (31,7 US GAL)

(kg) (lbs) (kg) (lbs) (kg) (lbs) (kg) (lbs)

160132,3 - - - - - -

Weight and Balance and Equipment List

Section 6

2

60 132,3 6,5 14,3 -- -­360132,3 6,5 14,3 30,2 66,6 -
460132,3 6,5 14,3 30,2 66,6 86,4 190,5
590198,5 - - - - - -

6

7

8

90 198,5 6,5 14,3 - - - -

90 198,5 6,5 14,3 30,2 66,6 - -

90 198,5 6,5 14,3 30,2 66,6 86,4 190,5

Page Date: 20. April 2002 6 - 5

Section 6
Weight and Balance and Equipment List

6.3 CENTER OF GRAVITY CALCULATION (SAMPLE PROBLEM)

[lbs]

2028

1985

1874

1808

1764

1654

1544

WEIGHT

Pilot´s Operating Handbook

EXTRA 300S

1433

45,0 50,0 55,0 60,0 65,0 70,0 ARM / CM

17,7 19,7 21,7 23,6 25,6 27,6 [INCHES]

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6.3.1 Sample

Take-off Condition
Pilot 90,0 kg (198,5 lbs)
Fuel in Acro Tank (9 L) 6,5 kg (14,3 lbs)
Fuel in Center Tank (42 L) 30,2 kg (66,6 lbs)
Fuel In Wing Tank (120 L) 86,4 kg (190,5 lbs)
Aircraft Empty Weight 610,0 kg (1345,1 lbs)

To find C/G, follow line "Pilot 90 KG" from Empty
Weight to Point 5.
Now follow line "Fuel 171 L" via point 6 and 7 to point 8.

FIND: Weight ~ 823 kg (1815 lbs)

Weight and Balance and Equipment List

Section 6

======== =========

823,1 kg (1815,0 lbs)

C/G ~ 58,8 cm (23,1 inch)

6.3.2 Weight and Balance Record Sheet

EMPTY WEIGHT
PILOT
FUEL ACRO TANK
FUEL CENTER TANK
FUEL WING TANK

ΣΣ

Σ ( W x X )

ΣΣ

XG = =

ΣΣ

Σ W

ΣΣ

WEIGHT ARM MOMENT

ΣΣ

Σ W =

ΣΣ

ΣΣ

Σ ( W x X ) =

ΣΣ

Page Date: 20. April 2002 6 - 7

Section 6
Weight and Balance and Equipment List

6.4 LOADING WEIGHTS AND MOMENTS

WEIGHT PILOT PILOT

Pilot REAR SEAT POSITION FRONT SEAT POSITION

+ Parachute ARM = 190 cm (75 inch) ARM = 170 cm (67 inch)
KG LBS MOMENT KG x CM (INCH x LBS)

60 132 11400 (9896) 10200 (8855)
65 143 12350 (10721) 11050 (9593)
70 154 13300 (11546) 11900 (10331)
75 165 14250 (12370) 12750 (11068)

Pilot´s Operating Handbook

EXTRA 300S

80 176 15200 (13195) 13600 (11806)
85 187 16150 (14020) 14450 (12544)
90 198 17100 (14845) 15300 (13282)

FUEL IN SYSTEM: MAX 171 LITER (45,1 US GAL.)

FUEL

ACRO & CENTER TANK WING TANKS

LITER KG KG x CM LITER KG KG x CM

(US GAL) (LBS) (IN LBS) (US GAL) (LBS) (IN x LBS)

9 (2,4) 6,5 (14,3) 168 (146) 10 (2,6) 7,2 (15,9) 238 (207)
20 (5,3) 14,4 (31,8) 531 (461) 20 (5,3) 14,4 (31,8) 475 (412)
25 (6,6) 18,0 (39,7) 696 (604) 40 (10,6) 28,8 (63,5) 950 (825)
30 (7,9) 21,6 (47,6) 861 (747) 60 (15,9) 43,2 (95,3) 1426 (1238)
35 (9,2) 25,2 (55,6) 1026 (891) 80 (21,1) 57,6 (127,0) 1901 (1650)
40 (10,6) 28,8 (63,5) 1191 (1034) 100 (26,4) 72,0 (158,8) 2376 (2063)
45 (11,9 32,4 (71,4) 1356 (1177) 120 (31,7) 86,4 (190,5) 2851 (2475)
51 (13,5) 36,7 (80,9) 1554 (1349)

6 - 8 Page Date: 20. April 2002

Pilot´s Operating Handbook
EXTRA 300S

6.5 WEIGHTS AND MOMENT LIMITS

EXAMPLE: AT 750 KG (1654 LBS) AND 44000 KGCM (38197 IN LBS)

CG LOCATION IS 58,7 CM (23,1 IN) AFT OF REF DATUM

WEIGHT

kg [lbs]

950 (2028)
900 (1985)

850 (1874)

Weight and Balance and Equipment List

Section 6

820 (1808)

800 (1764)

750 (1654)

700 (1544)

650 (1433)

MTOW
ACRO

EMPTY

600 (1323)

WEIGHT

45,0 50,0 55,0 60,0 65,0 70,0 ARM / CM
17,7 19,7 21,7 23,6 25,6 27,6 (INCH)

CENTER OF GRAVITY - CM (INCH) AFT OF REF DATUM

Page Date: 20. April 2002 6 - 9

Section 6
Weight and Balance and Equipment List

6.6 EQUIPMENT LIST

Pilot´s Operating Handbook

EXTRA 300S

EXTRA 300S S/N:

QTY ITEM MANUFACT. PART OR P/N WEIGHT ARM MARK IF REQUIRED (R)

1 Engine Textron Lycoming AEIO-540-L1B5 194.90 -0.72 R
1 Magneto L/H Slick 6251 or 6351 2.30 -0.15 R
1 Magneto R/H Slick 6250 or 6350 2.00 -0.15 R

1 Engine Textron Lycoming AEIO-540-L1B5D 194.90 -0.72 A
1 Magnetos Bendix D6LN-3000 5.20 -0.15 A

4 Shock Mounts Lord J 7764-20 1.70 -0.29 R
4 Shock Mounts Barry Controls 94016-02 1.70 -0.29 A
1 Exhaust System EXTRA/ 63104A0 7.65 -0.40 R

6 in 2 Sky Dynamics

2 Exhaust Gomolzig EA300 NSD 9.60 0.80 O

Silencer GO3-606500

1 Exhaust System Gomolzig EA300-606000 8.20 -0.39 A

6 in 1 with Silencer
1 Fuel Injector Bendix RSA-10 AD 1 3.90 -0.68 R
1 El. Fuel Pump Weldon Tool 8120-M or B8120-M 1.10 -0.04 R
1 Oil Cooler Stewart Warner 8406 R 1.40 -0.90 R
1 2. Oil Cooler Stewart Warner 8406 R 1.40 -0.20 R
1 Single Oilcooler, rear Niagara NDM 20009A 1.81 -0.22 A
1 Single Oilcooler, rear Aero Classics 8000353 1.65 -0.22 A
1 Set Fuel, Oil & Sens. div. MS28741 with 6.30 -0.21 R

Hoses in Eng. Comp. firesleeve
1 Set Fuel, Oil & Sens. Parker/Stratoflex PTFE Type 124J 4.90 -0.21 A

Hoses in Eng. Comp. or Aeroquip or AE466
1 Set Fuel, Oil & Sens. Parker/Stratoflex PTFE Type 124J 3.70 -0.15 A

Hoses in Eng. Comp. or Aeroquip or AE466

single Oil Cooler Sys.
1 Set Fuel Hoses div. MS28741 2.10 0.40 R

in Cabin Comp.
1 Set Fuel Hoses Parker/Stratoflex PTFE Type 124 1.40 0.40 A

in Cabin Comp. or Aeroquip or 666
1 Sens. Hoses Knapp/Hoerbiger HS3MA OR H3MM 0.15 0.82 A

(Oil, Fuel & MA Press)
1 RPM Vernier Control ACS Products Co. A-750-30-1080 0.65 0.60 R
1 Mixture Vernier Control ACS Products Co. A-750-20-1080 0.65 0.63 R
1 Throttle Control Teleflex Marine F303 03000 0.53 0.40 R
1 Propeller MT-Propeller MTV-9-B-C/C200-15 30.40 -1.15 R

1 Spinner MT-Propeller P-208-B R
1 Spinner MT-Propeller P-810-2 A

1 Propeller MT-Propeller MTV-14-B-C/C190-17 29.80 -1.15 O
1 Spinner MT-Propeller P-238-A O
1 Spinner MT-Propeller P-967 A

1 Cowling (GRP) incl. EXTRA 23205.01 & .02 9.80 -0.52 R

Air Intake Screen EXTRA 83802.1
1 Cowling (CRP) incl. EXTRA 23205.301 & .302 8.80 -0.52 A

Air Intake Screen EXTRA 83802.1
1 Cowling incl. EXTRA 83001.0 9.20 -0.53 A

Air Intake Screen

(KG) (m) INSTALLED OPTIONAL (O)

ALTERNAT. (A)

6 - 10 Page Date: 20. April 2002

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Pilot´s Operating Handbook
EXTRA 300S

Weight and Balance and Equipment List

Section 6

QTY ITEM MANUFACT. PART OR P/N WEIGHT ARM MARK IF REQUIRED (R)

1 Governor Woodward A- 210 988 1.10 -0.91 R
1 Governor MT-Propeller P-880-5 1.10 -0.91 A
7 Switches Cutler Hammer div. 0.28 1.31 R

7 Switches Kissling div. 0.28 1.31 A
11 Circuit Breaker Potter&Brumfield div. 0.50 1.29 R
11 Circuit Breaker ETA or Klixon div. 0.30 1.29 A

1 Main Bus Fuseholder MTA 03.00360 0.03 0.02 O

1 Main Bus Strip Fuse MTA 02.00300 O

(40 Amps)
1 PCB Auto Fuse EXTRA 83290.1 0.01 0.02 O
1 Fuel Cont. Probe VDO 226 801 015 001 G 0.12 0.33 R

Wing Tank
1 Fuel Cont. Probe VDO 224 082 007 004R 0.19 0.68 R

Center Tank
1 Fuel Cont. Ind. VDO 301 271 036 001 K 0.08 1.30 R

Wing Tank or 301 030 001 G
1 Fuel Cont. Ind. VDO 301 272 052 001 K 0.14 1.30 R

Acro Tank or 301 030 002 G
1 Ammeter VDO 190 004 039 002 0.08 1.31 R

or 190 037 002 G
1 Volt/Ammeter Electronics Intern. VA-1A 0.26 1.30 A
1 Shunt Electronics Intern. S-50 0.09 1.20 A

1 Volt/Ammeter Electronics Intern. VA-1A-50 0.22 1.30 A
1 RPM Indicator VDO 333 230 115 002 0.31 1.28 R

or 333 035 001 G
1 RPM Indicator digital Horizon P100-230-643-00 0.68 1.28 A
1 Magn. Dir. Ind. Airpath C 2300 0.25 1.30 R
1 Oil Press./ AMITEK or Christen 61943 0.51 1.30 R

Oil Temp. Ind.

1 Oil Press./ Westach 3DA3-3MM 0.14 1.30 A

Oil Temp. Ind. (3 1/8") or 3DA3-3KV
1 Oil Temp. Sender Westach W399-S9 0.08 -0.11 A
1 Oil Press Sensor Mediamate 387-100MM 0.12 0.04 A

or 387-100KV

1 Oil Press / Westach 2DA3-3MM 0.09 1.30 A

Oil Temp Ind. (2 1/4") or 2DA3-3KV
1 Oil Temp. Sender Westach W399-S9 0.08 -0.11 A
1 Oil Press Sensor Mediamate 387-100MM 0.12 0.04 A

or 387-100KV
1 Stall Sensor EXTRA 73106.1 0.07 0.27 R
1 Stall Warning Horn EMAG EM-S 110P 0.13 1.20 R
1 G-Meter EXTRA DSA 12 0.37 1.28 O
1 G-Meter Kollsman or Pioneer AN5745 0.40 1.28 O

or Bendix
1 G-Meter EZE Technologies DA-55 0.16 1.28 O
1 ELT and Antenna Pointer 3000-10 0.90 0.72 O
1 Turn & Bank Ind. United Instruments 9501-2 / TSO C3b 0.55 1.28 O
1 Turn & Bank Ind. Castleberry C101 / TSO C101T 0.55 1.28 O
1 Altimeter United Instruments UI5934PD-3 A.134 0.60 1.30 R

(KG) (m) INSTALLED OPTIONAL (O)

ALTERNAT. (A)

Page Date: 20. April 2002 6 - 11

Page Date: 31. January 2006

Section 6
Weight and Balance and Equipment List

Pilot´s Operating Handbook

EXTRA 300S

QTY ITEM MANUFACT. PART OR P/N WEIGHT ARM MARK IF REQUIRED (R)

1 Altimeter, metric Winter 4110 0.33 1.30 A
1 Altitude Encoder ACK A-30 0.15 0.95 O
1 Airspeed Ind. Winter 6533-321 0.21 1.29 R
1 Airsp. Ind., metric Winter 6531-321 0.21 1.29 A
1 Airspeed Ind. United Instruments UI8030 B.835 0.22 1.29 A
1 EGT/CHT Westach 2 DA 1 0.07 1.30 O

1 EGT Probe Westach 712-2 DWK 0.06 -0.37 O
1 CHT Probe Westach 712-7 DK 0.05 -0.20 O

1 Manifold Press. United Instruments UI6331-H.186 0.49 1.28 R

Fuel Flow Ind.
1 VHF Radio Becker AR 3201 0.90 1.26 R
1 VHF Radio Becker AR 4201 0.67 1.26 A
1 GPS / NAV / COM Garmin GNS 430 2.95 1.21 O
1 Transponder Bendix/King KT 73 1.64 1.21 O
1 Transponder Bendix/King KT 76A 0.89 1.21 O
1 Transponder Filser TRT-600 (LAST) 0.70 1.26 O
1 Transponder Filser TRT-800 0.70 1.26 O
1 Transponder Garmin GTX 327 0.95 1.21 O
1 Transponder Garmin GTX 330 1.50 1.21 O
1 Transponder Becker BXP6401-1 0.80 1.26 O
1 Transponder Becker BXP6401-2 0.80 1.26 O
1 Transponder Becker ATC-2000 1.20 1.21 O
1 Transponder Becker ATC-4401 0.73 1.26 O
1 Transponder Antenna Comant Industries CI 105 0.11 0.12 O
1 Transponder Antenna Bendix/King KA 60 0.11 0.12 O
1 COM Antenna Moba 210FA 0.10 4.07 R
1 COM Antenna Extra 83205A 0.10 4.07 A
1 COM Antenna Pointer P1 3001-10 0.05 4.07 A
1 Starter B&C Speciality BC 315-100-2 4.63 -0.85 R
1 Starter SKYTEC 149-12LS 3.65 -0.85 A

(Lycoming) (31A22 104)

1 Alternator 60 Amps Electrosystems ALX 8421 LS 5.90 -0.86 R

with bracket
1 Voltage Regul. Lamar B-00371-25 0.15 0.02 R
1 Low Volt. Monitor Lamar B-00378-4 R

1 Alternator 65 Amps Bosch 0 120 489 935 4.60 -0.86 A
1 Alternator 55 Amps Bosch 0 120 489 917 4.20 -0.86 A
1 Alternator 55 Amps Bosch 0 120 489 469 4.20 -0.86 A
1 Battery Sonnenschein Dryfit A 212/28G 10.70 0.17 R
1 Battery Concorde RG-25XC 10.40 0.17 A
1 Batt. Charger Plug EXTRA 146 19 20 0.02 0.12 O
1 External Power Recept. Div. AN2552-3A 1.46 0.76 O
1 Ext. Power Solenoid Switches Kidde 22735 0.40 0.02 O
1 Ext. Power Solenoid White-Rodgers 70-111-225-5 0.40 0.02 O

(cont. operation)

(KG) (m) INSTALLED OPTIONAL (O)

ALTERNAT. (A)

6 - 12 Page Date: 20. April 2002

Page Date: 31. January 2006

Page Date: 20. September 2006

Pilot´s Operating Handbook
EXTRA 300S

Weight and Balance and Equipment List

Section 6

QTY ITEM MANUFACT. PART OR P/N WEIGHT ARM MARK IF REQUIRED (R)

1 Main Bus Solenoid White-Rodgers 70-111-226-5 0.40 0.02 R
1 Starter Solenoid Switches Kidde 22735 0.40 0.02 R
1 Low Voltage Light OAK MS25041-2 0.02 1.31 R
1 Ignition TCM 10-357200-1 0.15 1.30 R

Switch
2 Wheel Cleveland 40-151 4.00 0.16 R
2 Main Wheel Tires Div 5.00-5 / 6PR 3.90 0.16 R
1 Tail Wheel 5" EXTRA steerable 5.50 4.91 A
1 Tail Wheel 5" EXTRA free swivel type 5.50 4.91 R
1 Tail Wheel 6" Assy Special Products 5.90 4.91 A

(Soft) Aviation Inc.
2 Brake Assy Cleveland 30-164 1.40 0.16 R
2 Brake Cyl. Cleveland 10-20 or 10-20E 0.55 0.89 R
2 Brake Cyl. Matco MC-4E 0.55 0.89 A
1 Brake Fluid Reservoir EXTRA 53301.1 0.20 0.03 R
1 Brake Fluid Reservoir ACS A-315 0.20 0.04 A
1 Safety Belt Hooker 1 011 230 3.30 1.95 R

Assy with ratchet
2 NAV/STROBE LTS Whelen A 600-PG/PR-14 0.23 0.56 R
2 Power Supply Whelen A490T 0.54 0.56 R
2 Electric Actuator SKF CARR 3.25 0.65 R

Pedal Adjust. 22x200x1/D12B
1 Long Range Tank EXTRA 84901 1.80 0.38 O
1 Fuel Selector Spruce 108HD-04 0.30 0.56 R
1 Fuel Selector Allen 6 S 122 0.19 0.56 A
1 Safety Cover EXTRA 84803.1 2.53 2.80 O

(Polycarbonate)
1 Dual Pump EXTRA 84100 6.40 0.20 O

Smoke System

without Pumps
2 Smoke Oil Pump ITT Jabsco 8860-1203 3.60 0.20 O

(Inject. and Refill)
2 Smoke Oil Pump ITT Jabsco 23620-3003 4.40 0.20 O

(Inject. and Refill)
1 Smoke Oil Pump Johnson F3B-19 (12V) 2.00 -0.05 O

(Injection)
1 Smoke Oil Pump Johnson F2P10-19 (12V) 1.65 0.35 O

(Refill)
1 Single Pump EXTRA 84112 6.80 0.19 O

Smoke System

incl. Pump Marco UP3/OIL 12V
1 Airtow Hook EXTRA/TOST 83607A0 0.50 5.10 O

1/2 Sighting Dev. LH/RH EXTRA 84801.10 each 0.44 1.25 O

1 Aresti-Card Holder EXTRA Assy 0.09 1.32 O
2 Wing Tie Down Rings EXTRA 83801.2-01 0.04 0.95 O

(KG) (m) INSTALLED OPTIONAL (O)

ALTERNAT. (A)

Page Date: 20. April 2002 6 - 13

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Section 6
Weight and Balance and Equipment List

Pilot´s Operating Handbook

EXTRA 300S

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6 - 14 Page Date: 20. April 2002

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Description and Operation of Aircraft and Systems

Section 7

SECTION 7

DESCPRIPTION AND OPERATION

OF AIRCRAFT AND SYSTEMS

Table of Contents

Paragraph Page

SECTION 7 DESCPRIPTION AND OPERATION OF AIRCRAFT AND SYSTEMS

7.1 THE AIRCRAFT .................................................................................................................. 7-3

7.2 FUSELAGE ......................................................................................................................... 7-3

7.3 WINGS ................................................................................................................................ 7-4

7.4 EMPENNAGE ..................................................................................................................... 7-4

7.5 FLIGHT CONTROL SYSTEM............................................................................................. 7-5

7.5.1 Primary Control System.......................................................................................................7-5

7.5.2 Longitudinal Flight Control System ...................................................................................... 7-5

7.5.3 Lateral Flight Control System .............................................................................................. 7-5

7.5.4 Directional Flight Control System ........................................................................................ 7-5

7.5.5 Secondary Control............................................................................................................... 7-5

7.6 INSTRUMENTATION .......................................................................................................... 7-5

7.6.1 Instrument Panel................................................................................................................. 7-6

7.7 LANDING GEAR................................................................................................................. 7-7

7.8 SEA TS, SEA T BELTS ......................................................................................................... 7-7

7.9 CANOPY ............................................................................................................................. 7-8

7.10 POWER PLANT.................................................................................................................. 7-8

7.10.1 Engine ................................................................................................................................. 7-8

7.10.2 Oil System........................................................................................................................... 7-9

7.10.3 Engine Installation ............................................................................................................... 7-9

7.10.4 Propeller.............................................................................................................................. 7-9

7.10.5 Throttle................................................................................................................................ 7-9

7.10.6 Mixture ................................................................................................................................ 7-9

7.10.7 RPM-Control ....................................................................................................................... 7-9

7.10.8 Fuel Selector Valve............................................................................................................ 7-10

7.10.9 Exhaust Systems (Optional) .............................................................................................. 7-10

7.11 FUEL SYSTEM ................................................................................................................. 7-10

7.12 ELECTRICAL SYSTEM .................................................................................................... 7-11

7.13 CABIN ENVIRONMENT CONTROL ................................................................................. 7-13

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Section 7
Description and Operation of Aircraft and Systems

Pilot´s Operating Handbook

EXTRA 300S

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7 - 2 Page Date: 20. April 2002

Pilot´s Operating Handbook
EXTRA 300S

7.1 THE AIRCRAFT

The aircraft EXTRA 300/S is designed and developed by EXTRA Flugzeugproduktions- und
Vertriebs- GmbH, Dinslaken 46569 Hünxe, Federal Republic of Germany, in accordance
with the U.S. Federal Aviation Regulations, part 23, categories normal and acrobatic to fullfill
the primary flight training, normal operation rules and acrobatic training up to the unlimited
acrobatic level.

EXTRA 300/S is a light weight, robust, single piston-engined, one-seat aircraft with a
fuselage structure in tig-welded steel-tube construction.

Description and Operation of Aircraft and Systems

Section 7

SECTION 7

DESCPRIPTION AND OPERATION

OF AIRCRAFT AND SYSTEMS

The landing gear, wing, and tail are made of epoxy, reinforced with glass- and carbonfiber.
The items are qualified up to 72°C.

The standard aircraft is designed to operate within a range of ambient air temperature from ­20°C to +44°C (-4°F => 111°F) at sea level. It is possible to start the engine using the
aircraft battery at -20°C (-4°F) without preheating. Below -10° C (+14°F) OAT a special oil
breather line must be adapted (available as kit).

7.2 FUSELAGE

The fuselage structure consists of a steel tube construction integrating the wing and
empennage connections as well as the seat. The lower front part of the fuselage and the
sides below the wing are faired with aluminium sheet metal. Within the exhaust area
stainless steel sheet metal is used. To improve pilots view for acrobatic maneuvers a
Lexan® window is installed in the lower fuselage skin. The rear part of the fuselage is
covered with Ceconite® 102.
The upper fuselage body surface is one part from firewall to vertical stabilizer including the
correlated canopy frame. It consists of a kevlar laminate.
The canopy frame itself is constructed by carbon laminate. The canopy is one part, opens to
the right and is held in the open position by a belt. Emergency jettisonning is achieved by
simply unlatching the canopy. For additional pilots protection a roll bar is installed behind the
pilots seat.

Page Date: 20. April 2002 7 - 3

Page Date: 31. January 2006

Section 7
Description and Operation of Aircraft and Systems

7.3 WINGS

The wing is of CRP construction. The dual chamber main spar - being a fail safe design ­consists of carbon roving caps combined with CRP webs. Core foam is a PVC foam
(Divinycell HT 50). The wing shell is built by a Honeycomb sandwich with CRP laminates.
To improve surface quality and for protection of the carbon wing shell an outer layer of glass
fibre, except of the tank area, is applied. In the area of the wing tanks is a layer of CRP
laminate with an incorporated aluminium thread bonded to the metal fuselage structure as
means of lightning protection. To prevent buckling of the shell plywood ribs are installed.
These ribs are permanently protected from environmental effects by an epoxy coating.
The connection to the fuselage is arranged by two bolts piercing through the spar parallel to
the centerline of the fuselage and two brackets at the rear spars.
Integral fuel cells are provided in the leading edge of the wing extending from the root ribs to
half the span of each R/L and L/H wing.
The ailerons are supported at three points in spherical bearings pressed into aluminium
brackets.
To reduce pilot's hand forces the hinge line of the ailerons is positioned 25% of the aileron
depth at the root and 21,5% at the tip. Furthermore the ailerons are equipped with "spades"
to decrease pilot forces. Ailerons are controlled via the center bracket.
To prevent flutter the ailerons are weight balanced in the overhanging leading edge.

Pilot´s Operating Handbook

EXTRA 300S

7.4 EMPENNAGE

The EXTRA 300/S possesses a cruziform empennage with stabilizers and moveable control
surfaces. The rudder is balanced aerodynamically at the tip. Spars consist of PVC foam
cores, CRP caps and GRP laminates. The shell is built by honeycomb sandwich with GRP
laminates. Buckling is prevented by plywood ribs.
Deviating from the other control surfaces the elevator, due to aerolastic reasons, entirely is
built by CRP. On the R/H elevator half a trim tab is fitted with two hinges. The control
surfaces are mounted in spherical bearings (exception: Trim tab). To prevent flutter rudder
and elevator are mass balanced. The balance weight for the rudder is installed in the rudder
tip while the balance weight for the elevator is mounted on the elongated center bracket of
the elevator extending into the fuselage.

7 - 4 Page Date: 20. April 2002

Pilot´s Operating Handbook
EXTRA 300S

7.5 FLIGHT CONTROL SYSTEM

7.5.1 PRIMARY CONTROL SYSTEM

The EXTRA 300/S is standard equipped with conventional stick-type control columns and
electric adjustable rudder pedals. The primary control surfaces are operated through a direct
mechanical linkage.

7.5.2 LONGITUDINAL FLIGHT CONTROL SYSTEM

The stick bearing is housed in a torque tube, which is also linked to the lateral flight controls.
The stick movements are transferred to the elevator by a push-pull rods.

7.5.3 LATERAL FLIGHT CONTROL SYSTEM

Push-pull rods are connected by sealed ball bearings from the torque tube to the ailerons.
The ailerons are statically as well as dynamically balanced. (Dynamically with spades).
The ailerons are supported by lubricated, sealed bearings.

Description and Operation of Aircraft and Systems

Section 7

7.5.4 DIRECTIONAL FLIGHT CONTROL SYSTEM

The rudder pedals with brake pedals are adjustable and operate the rudder through a cable
system. Springs keep the cables under tension when the pedals are not operated.

The pedal adjustment is archieved with electric linear actuators. The pedal adjustment
system provides an in-flight capability to adjust the pedals according the the pilot size and
operation e. i. for long cross country flight a mor relaxed, streched seating position is
possible. A full travel from the most rearward to the most forward position takes
approximately 15sec.

7.5.5 SECONDARY CONTROL

The elevator trim control is located on the right side in the cockpit. The actuation is a fail
safe design to prevent flutter in case of a single control joint failure.
The canopy lock is operated from the outside by a handle on left side of the canopy by
reaching into the cockpit through the window. The handle is used for locking as well as for
normal operation and for emergency release.
The starter/magneto switch is located on the left side of the instrument panel.

7.6 INSTRUMENTATION

Standard equipment incorporates a magneto compass, an airspeed indicator, altimeter, fuel
gauges, engine-RPM and manifold pressure / fuel flow indicator as well as an ampermeter
and a low voltage warning. Furher dual instruments exhaust gas / cylinderhead temperature
indicator and oil temperature / pressure indicator are installed.
Instruments and placards can be provided with markings in either metric or English units.
The colour markings in instruments follow US-FAR, part 23 recommendation
(see section 2).

Page Date: 20. April 2002 7 - 5

Section 7
Description and Operation of Aircraft and Systems

7.6.1 INSTRUMENT PANEL

For instrumet panel arrangement of the cockpit refer to Fig. 7.6.1, which includes standard
and optional equipment marked as such.

Fig. 7.6.1

1 2 / 40 3 4 5 6 7 8 9

12 11

13

Pilot´s Operating Handbook

EXTRA 300S

10

14 15 16 17 23 - 32 18 19 20 21 22

41 / 2*

Standard Optional Position Item

x 1 Magneto Selector Switch & Starter
x 2 Amperemeter
x 3 Altimeter
x 4 Air Speed Indicator
x 5 Manifold Pressure / Fuel Flow
x 6 Magn. Direction Indicator
x 7 Oil Pressure / Oil Temperature
x 8 G-Meter
x 9 EGT / CHT
x 10 RPM Indicator
x 11 COM
x 12 Fuel Quantity Center Tank
x 13 Fuel Quantity Wing Tank
x 14 Master Switch
x 15 Field Switch
x 16 Low Voltage Monitor
x 17 Boost Pump Switch
x 18 Nav Light Switch
x 19 Strobe Light Switch
x 20 Radio Master Switch
x 21 Left Pedal Adjustment Switch
x 22 Right Pedal Adjustment Switch
x 23 Circuit Breaker Stall Warninig
x 24 Circuit Breaker Alt Field
x 25 Circuit Breaker Alt Output
x 26 Circuit Breaker Starter

7 - 6 Page Date: 20. April 2002

Pilot´s Operating Handbook
EXTRA 300S

Standard Optional Position Item

x 27 Circuit Breaker Boost Pump
x 28 Circuit Breaker Nav Lights
x 29 Circuit Breaker Strobes
x 30 Circuit Breaker Radio
x 31 Circuit Breaker Fuel & RPM Gauges
x 32 Circuit Breaker Pedal Adjustment
x 33 RPM control, Prop governor
x 34 Mixture control
x 35 Throttle lever
x 36 Stick
x 37 Radio button
x 38 Fuel shutoff valve
x 39 Trim lever and indicator

Description and Operation of Aircraft and Systems

Section 7

x 40 Turn & bank indicator
x 41 GPS

This list may be modified by the minimum equipment requirements of individual
certifying authorities!

7.7 LANDING GEAR

The landing gear is a composite construction with a multichamber fiberglass spring in a tail­wheel design. The main wheels have a size of 5-5.50 and they are equipped with hydraulic
disc brakes. The tail wheel has a solid rubber tire with full-swivel capability.

7.8 SEATS, SEAT BELTS

The seat is an ergonomical shaped carbon composite construction. It´s back rest position
and angle is mechanically adjustable on ground by quickpins and bolts. The lower seat
surface itself is fixed.
Seat to pedal distance can be varied on ground and in flight using the electrically actuated
pedal adjustment system. Each pedal can be adjust separate by a switch on the instrument
panel.
The seat belt assembly consists of right and left shoulder straps, two right and two left lap
belts and a negative g-strap. All belts are adjustable. The lap belts have a separate single
point release for redundant safety during acrobatic maneuvers. If one release is opened
unintentionally the second one guarantees full safety. To assure safe operation one release
must be closed to the right the other one to the left. During acrobatic maneuvers the seat
belt system should be tightened firmly.

NOTE:

NOTE

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Section 7
Description and Operation of Aircraft and Systems

7.9 CANOPY

The canopy is manufactured in one section. The canopy can be manually operated and
opened by lifting to the right.
Interior canopy locking handles, located on the left side on the canopy must be pulled
together to unlock the canopy from the inside. To open the canopy from the outside there
are no seperate handles, this means it must be opened by reaching through the small
window (bad weather window) and proceed as mentioned above (interior opening).

7.10 POWER PLANT

7.10.1 ENGINE

The power plant consists of one Textron-Lycoming six-cylinder, horizontally opposed,
aircooled, direct drive, fuel injection engine type with inverted oil system. The T/O Power is
300 HP at 2700 RPM.

Engine specification: a) Textron - Lycoming AEIO-540-L1B5

b) Textron - Lycoming AEIO-540-L1B5D

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For the present TBO refer to latest issue of Textron-Lycoming
SERVICE LETTER No. L 201.

The AEIO-540-L1B5 (D) engine is equipped with special antivibration counterweights.
The following accessories are included in the power plant

installation:

-Fuel Injector: Bendix

-Magnetos: Slick

-Alternator: Electrosystem

-Starter: B&C

-Fuel pump: Gates Lear

-Shielded ignition system

-Propeller governor drive

-Transistor voltage regulator

The engine is operated with the following manual controls:

-Throttle control

-RPM control

-Fuel mixture control

The propeller governor monitors the RPM automatically and prevents overspeeding. In the
event that oil pressure is lost the propeller is automatically adjusted to coarse pitch in order
to avoid overspeeding.

The use of 100/130 aviation grade fuel (AVGAS 100/100LL) is the minimum grade
recommended by the manufacturer of the engine.

For continuous operation 115/145 aviation fuel is the maximum grade.

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7.10.2 OIL SYSTEM

The oil is cooled by a Two Cooler System mounted on the left hand side in the engine
compartment.
Alternatively a Single Cooler System is available. In this case the oil is cooled by one oil
cooler mounted on the aft, right hand side of the engine. The oil level is determined by a dip­stick.

Oil capacity:
Max sump capacity: 16 qts.

Min sump capacity: -Acro 12 qts.

For temperatures and oil grades refer to Section 1.7.

7.10.3 ENGINE INSTALLATION

Description and Operation of Aircraft and Systems

Section 7

-Normal 9 qts.

The engine is mounted with four shock-mounts (Type LORD or BARRY CONTROLS) to the
tig-welded steel tube engine support, which is attached to the fuselage with four bolts on the
firewall axis.

The engine cowling is divided into two parts, a lower and an upper part both made of glass­fibre reinforced epoxy. The parts are fixed by a number of screws and the upper cowling has
a separate hatch for easy access to the oil dip-stick.

7.10.4 PROPELLER

The propeller is a 4-blade wood composite, constant speed propeller type MTV-14-B-C/
C190-17 with a diameter of 1,9 m, or optional with a 3-blade propeller type MTV-9-B-C/
C200-15 with a diameter 2,0 m .

7.10.5 THROTTLE

Control lever (cub-type) mounted on the left side in cockpit.

7.10.6 MIXTURE

Vernier control located at right side of cockpit (red knob).

7.10.7 RPM-CONTROL

Vernier control located at left side of cockpit (blue knob) Push-pull type with friction lock on
the left side of the rear cockpit.
Preselection of RPM possible due to constant speed governor.

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Section 7
Description and Operation of Aircraft and Systems

7.10.8 FUEL SELECTOR VALVE

A rotary fuel selector valve is mounted behind the firewall on the right side of the fuselage. A
torque tube connects the valve to the cockpit handle. Pull and turn the handle 90° to open
the valve to the Acro & Center tank. A further 90° turn switches to the Wing tank fuel supply.

Position down = CLOSED
Position left = ACRO & CENTER TANK
Position up = WING TANK

7.10.9 EXHAUST SYSTEMS (OPTIONAL)

Optionally the EA 300/S can be equipped with an additional silencer system type Gomolzig.
The attachment is integrated in the fuselage structure. Thus no modifications are necessary
to install the silencer system.
Alternatively a complete 6 in 1 System with integrated silencer is available.

7.11 FUEL SYSTEM

The fuel system consists of two separate, independent tanks:

- Acro & Center tank in the fuselage

- Wing tank (LH and RH)

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Wing tank:
The root section of each wing - in front of main spars forms an integral fuel tank providing
two interconnected tanks with 120 liters (31,7 US GAL.) total capacity. Each side of the wing
has a 2" diameter filler cap for gravity refueling. The wing tank can be completely emptied in
flight but the normal amount of unusable fuel is approximately 2 Liters
(0.5 US Gallon).

Acro & center tank:
An Acro tank 9 liters (2,3 US Gal.) is mounted in the fuselage just behind the firewall and the
Center tank 42 liters (11,1US Gal.) just behind the main spar of the wing. The Acro tank is
connected with the center tank in a gravity feed system. The center tank has a 2" diameter
filler cap for gravity refueling. Unusable fuel is approximately 2 liters (0,5 US Gal.)

Adequate venting is provided in each tank to a main ventilation-tube, ending outside the
fuselage at the right side.

In addition to the engine driven fuelpump an electrically driven auxiliary fuel pump (boost
pump) with by-pass and having sufficient capacity to feed the engine at take-off power is
fitted as a safety device against failure of the engine-driven pump. The boost pump switch is
located on the instrument panelt.

A fuel filter with drain is installed between the fuel selector valvef and the boost pump.
Separate drains are located at the lowest point of each tank system.

Normal float type transducers and electrically operated fuel indicators are used.

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7.12 ELECTRICAL SYSTEM

The electrical power generation system consists of a 12 V alternator with rectifier and
transistor voltage regulator. The alternator is mounted on and driven by the engine.

The field current is controlled by the voltage regulator to give a nominal output of 13,8 V
under all load conditions.

Circuit protection against over-voltage is provided by the voltage regulator.
The maximum load taken from the alternator is 40 amp.
The system is equipped with a low voltage monitor that gives a visual warning if the aircraft

voltage drops below 12,75 V.
The master-switch is located on the instrument panel.

A 12 V leak proof battery is connected across the alternator output to stabilize the supply
and to maintain all essential services in the event of an alternator failure and when the
engine is not operating. The battery is mounted behind the firewall.

Description and Operation of Aircraft and Systems

Section 7

All electrical circuits are protected by circuit breakers located on the instrument panel and
they are easily accessible to the pilot during flight.

The electrical system is adequately suppressed to ensure satisfactory operation of the radio
equipment.

All wires, switches, circuit breakers etc. are manufactured to related aeronautical
specifications.

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Section 7
Description and Operation of Aircraft and Systems

Standard Equipment shown only

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7.13 CABIN ENVIRONMENT CONTROL

A ventilation system in the canopy is provided for the supply of fresh air to the cabin. The
bad weather window is equipped with a ventilation scoop to provide supply of fresh air to the
cabin. Additionally, to the left and right of the cockpit eyeball-type adjustable vents are
installed.

Description and Operation of Aircraft and Systems

Section 7

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Section 7
Description and Operation of Aircraft and Systems

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Handling, Servicing and Maintenance

Section 8

SECTION 8

HANDLING, SERVICING AND MAINTENANCE

Table of Contents

Paragraph Page

SECTION 8 HANDLING , SER VICING AND MAINTENANCE

8.1 INTRODUCTION................................................................................................................. 8-3

8.2 AIRPLANE INSPECTION PERIODS................................................................................... 8-3

8.3 PILOT CONDUCTED PREVENTIVE MAINTENANCE ....................................................... 8-3

8.4 AL TERA TIONS OR REPAIR ...............................................................................................8-3

8.5 SERVICING......................................................................................................................... 8-3

8.6 GROUND HANDLING......................................................................................................... 8-4

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Handling, Servicing and Maintenance

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HANDLING, SERVICING AND MAINTENANCE

8.1 INTRODUCTION

a) The airplane owner should establish contact with the dealer or certified service station for

service and information.

b) All correspondence regarding the airplane must include its serial number which is

stamped on a plate on the L/H rear part of the fuselage.

c) A service manual with revision service may be procured from the manufacturer.

8.2 AIRPLANE INSPECTION PERIODS

Handling, Servicing and Maintenance

Section 8

SECTION 8

As required by national operating rules all airplanes must pass a complete annual
inspection every twelve calendar months. In addition to the annual inspection airplanes
must pass a complete inspection after every 100 flights hours with a minor check after
50 and 25 hours.

The Airworthiness Authority may require other inspections by the issuance of airworthiness
directives applicable to the aircraft, engine, propeller and components. The owner is
responsible for compliance with all applicable airworthiness directives and periodical
inspections.

8.3 PILOT CONDUCTED PREVENTIVE MAINTENANCE

Pilots operating the airplane should refer to the regulations of the country of certification for
information of preventive maintenance that may be performed by pilots. All other
maintenance required on the airplane is to be accomplished by appropriately licensed
personnel. Airplane dealer should be contacted for further information

Preventive maintenance should be accomplished with the appropriate service manual.

8.4 ALTERATIONS OR REPAIR

Alterations or repairs of the airplane must be accomplished by licensed personel.

8.5 SERVICING

In addition to the airplane inspection periods (8.2) information for servicing the aircraft with
proper oil and fuel is covered in Section 2 (Limitations) and Section 7 (Descriptions and
Operation).

Page Date: 20. April 2002 8 - 3

Section 8
Handling, Servicing and Maintenance

8.6 GROUND HANDLING

a) Due to its low weight and the free swiveling tail wheel two persons can easily move the
airplane by hand.

b) To tie down the airplane M6 nut plates are provided in the wing tips where ring bolts can
be screwed in. The tail wheel leg can be used as third point to tie down the airplane.
If the aircraft is parked in the open, it must be protected against the effects of weather, the
degree of protection depending on severity of the weather conditions and the expected
duration of the parking period. When the airplane is parked in good weather conditions for
less than a half day park the aircraft headed into the wind and place wheel chocks at the
main wheels.

c) To level the aircraft, the tail wheel is rested on a balance and jacked to a position that the
fuselage reference line (upper fuselage stringer tube) is horizontal. There are two engine
hoists provided on the top of the engine which can be used to lift the airplane with a crane.
(Tail wheel resting on ground)

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EA - 300S

Section 9

Supplements

SECTION 9

SUPPLEMENTS

Doc-No. EA-04701.1

Table of Contents

Section Pages

9 Supplements............................................................................................................ 4 p.

901 F Steerable Tail Wheel ............................................................................................... 4 p.

902 F Electronic Accelerometer .......................................................................................10 p.

903 F Emergency Locator Transmitter ............................................................................8 p.

904 F External Power ........................................................................................................ 6 p.

905 F Digital RPM Indicator .............................................................................................. 6 p.

906 F Long Range Wing Tank Capacity........................................................................... 6 p.

907 F Airtow Hook ............................................................................................................. 8 p.

908 F Smoke System......................................................................................................... 6 p.

909 F Reserved

910 F Reserved

911 F Reserved

912 F FILSER TRT 600 Transponder................................................................................ 8 p.

913 F FILSER TRT 800 Transponder................................................................................ 8 p.

914 F GARMIN GTX 327 Transponder.............................................................................. 6 p.

915 F GARMIN GTX 330 Transponder.............................................................................. 8 p.

916 F BENDIX/KING KT 76A Transponder ....................................................................... 6 p.

917 F BENDIX/KING KT 73 Transponder .........................................................................8 p.

918 F BECKER ATC 2000 Transponder ........................................................................... 6 p.

919 F BECKER ATC 4401 Transponder ........................................................................... 8 p.

920 F BECKER BXP 6401 Transponder ........................................................................... 10 p.

SECTION 9 SUPPLEMENTS

9 SUPPLEMENTS ....................................................................................................................3

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Section 9
Supplements

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EA - 300S

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