Jabiru J400 User manual

Publication JP OM15 Jabiru J400
Owners Manual Section: 0
Section: 0COVER PAGE
DETAILS OF MANUFACTURER
Jabiru Aircraft Pty Ltd
Airport Drive
Bundaberg Queensland 4670
Australia
Postal Address:
P.O. Box 5186
Bundaberg West Queensland 4670
Australia
Telephone:
07 4155 1778 (int. [phone])
Email:
[email protected]
AIRCRAFT TYPE & MODEL
Type: JABIRU
Model: J400
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APPROVAL PAGE
Nationality and Registration Marks Australia
Manufacturer Jabiru Aircraft Pty Ltd
Designation of Aircraft J400
Registration Number
Aircraft Serial Number
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TABLE OF CONTENTS
SECTION
General 1
Limitations 2
Emergency Procedures 3
Normal Procedures 4
Performance 5
Weight and Balance Statement 6
Supplements 7
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AMENDMENT RECORD SHEET
Amendment No. Paragraph
(s)Affected
Signature. Date of
Incorporation
Incorporation of a General Amendment should be certified by inserting the date of
incorporation & signature in the appropriate columns.
All amendments should be embodied consecutively.
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INTRODUCTORY PAGE
This Owners Manual is provided by Jabiru Aircraft Pty Ltd as a guide to the
operation of the Jabiru J400 model aircraft. As the J400 model is an experimental
amateur built kitplane, the characteristics, performance, limitations and other
information may vary between individual aircraft. As part of the test flight program,
the Owner must verify the characteristics, performance limitations and other
information is relevant to their particular aircraft and amend any guidance figures
that are provided in this Manual
Jabiru Aircraft Pty Ltd accepts no responsibility for the guidance data and
information provided in this Manual.
This Owners Manual applies only to the particular aircraft identified by the
registration marking and serial number on the Approval Page and contains the
airworthiness limitations and essential operating data for this aircraft.
Special operations requiring additional limitations and instructions are listed in the
"Supplements Section" and this section shall be consulted before undertaking any
such operations. For operating information not included in this manual, reference
should be made to the appropriate operations or manufacturer's manuals.
The Owner Manual shall be carried in the aircraft on all flights.
The pilot in command of the aircraft shall comply with all requirements, procedures
and limitations with respect to the operation of the aircraft set out in the Owners
Manual for the aircraft.
Amendments shall be issued by Jabiru as necessary and will take the form of
replacement pages, with the changes to the text indicated by a vertical line in the
margin together with the amendment date at the bottom of the page.
Interim/Temporary amendments may be issued in the same manner and are to be
inserted as directed. These amendments will take precedence over the stated
affected page. It is the owner's responsibility to incorporate in this manual all such
amendments.
This aircraft has been qualified on the basis of the equipment fitted at the time of
qualification.
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REVISIONS
Revisions to this Manual will be distributed to all JABIRU Service Agents and to
owners of aircraft registered with JABIRU AIRCRAFT Pty Ltd.
Revisions should be examined immediately upon receipt and incorporated in this
Manual.
NOTE
It is the responsibility of the owner to maintain this Manual in a current status when it
is being used for operational purposes.
Owners should contact JABIRU AIRCRAFT PTY LTD whenever the revision status
of their Manual is in question.
A revision bar will extend the full length of new or revised text and/or illustrations
added on new or presently existing pages. This bar will be located adjacent to the
applicable revised area on the outer margin of the page.
All revised pages will carry the revision number and the date on the applicable page.
DEFINITIONS
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AIRFIELD PRESSURE
ALTITUDE
The Airfield Pressure Altitude is that altitude registered
at the surface of the aerodrome by an altimeter with the
pressure subscale set to 1013 millibars
INDICATED AIRSPEED
(I.A.S.)
Indicated airspeed, which is the reading obtained from
an airspeed indicator having no calibration error.
TAKEOFF SAFETY
SPEED
The Takeoff Safety Speed is a speed chosen to ensure
that adequate control will exist under all conditions,
including turbulence and sudden and complete engine
failure, during the climb after takeoff.
LANDING SAFETY
SPEED
The Landing Safety Speed is the speed chosen to
ensure that adequate control will exist under all
conditions, including turbulence, to carry out normal
flare and touchdown.
NORMAL OPERATING
SPEED This speed shall not normally be exceeded. Operations
above the Normal Operating Speed shall be conducted
with caution and only in smooth air.
Va MANOEUVRING
SPEED
Maximum for manoeuvres involving an approach to
stall conditions or full application of the primary flight
controls.
KCAS KNOTS
CALIBRATED AIRSPEED
Indicated airspeed corrected for position and
instrument error and expressed in knots. KCAS is equal
to KTAS in standard atmosphere at sea level
KIAS KNOTS
INDICATED AIRSPEED
The speed shown on the airspeed indicator and
expressed in knots.
KTAS KNOTS TRUE
AIRSPEED
The airspeed expressed in knots relative to undisturbed
air which is KCAS corrected for altitude and
temperature.
V fe MAXIMUM FLAP
EXTENDED SPEED
The highest speed permissible with wing flaps in the
prescribed extended position.
V no MAXIMUM
STRUCTURAL CRUISING
SPEED
The speed that should not be exceeded except in
smooth air, and then only with caution.
V ne NEVER EXCEED
SPEED The speed limit that may not be exceeded at any time.
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V s1 STALLING SPEED The stall speed or minimum steady flight speed at
which the airplane is controllable in a specified
configuration.
V so STALLING SPEED
LANDING
CONFIGURATION
The stall speed or minimum steady flight speed at
which the airplane is controllable in the landing
configuration at the most forward centre of gravity.
V x BEST ANGLE-OF-
CLIMB SPEED
The speed which results in the greatest gain of altitude
in a given horizontal distance.
V y BEST RATE-OF-
CLIMB SPEED
The speed which results in the greatest gain in altitude
in a given time.
METEOROLOGICAL TERMINOLOGY
OAT OUTSIDE AIR
TEMPERATURE
The free static air temperature. It is expressed in either
degrees Celsius or degrees Fahrenheit.
STANDARD
TEMPERATURE
Standard Temperature is 15 degrees C at sea level
pressure altitude and decreases by 2 degrees C for
each 1000 feet of altitude.
PRESSURE ALTITUDE The altitude read from the an altimeter when the
altimeter's barometric scale has been set to 1013 mb
(29.92 inches of mercury).
ENGINE POWER TERMINOLOGY
BHP BRAKE
HORSEPOWER
The power developed by the engine.
RPM REVOLUTIONS
PER MINUTE
Engine speed.
STATIC RPM The engine speed attained during a full-throttle engine
runup when the airplane is on the ground and
stationary.
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AIRPLANE PERFORMANCE AND FLIGHT PLANNING
TERMINOLOGY
MAXIMUM CROSSWIND
VELOCITY
The velocity of the crosswind component for which
adequate control of the airplane during takeoff and
landing was actually demonstrated during the
certification tests. The value shown is limiting.
USEABLE FUEL The fuel available for flight planning
UNUSABLE FUEL The quantity of fuel that cannot be safely used in flight
LPH LITRES PER
HOUR
The amount of fuel ( in litres ) consumed per hour
NMPL NAUTICAL
MILES PER LITRE
The distance ( in nautical miles ) which can be
expected per litre of fuel consumed at a specific engine
power setting and/or flight configuration.
g The acceleration due to gravity.
WEIGHT AND BALANCE TERMINOLOGY
STATION Only two load stations are specified: ie Seat Station
which is the centre of the fixed seats and Fuel Station
which is the centre of the fixed fuel tank.
C.G. CENTRE OF
GRAVITY
The point at which an airplane, or equipment, would
balance if suspended.
C.G. LIMITS The extreme centre of gravity locations within which the
airplane must be operated at a given weight.
STANDARD EMPTY
WEIGHT
The weight of a standard airplane, including unusable
fuel, full operating fluids and full engine oil.
BASIC EMPTY WEIGHT The standard empty weight plus the weight of optional
equipment.
USEFUL LOAD - The difference between ramp weight and the basic
empty weight.
MTOW MAXIMUM
TAKEOFF WEIGHT
The maximum weight approved for the start of the
takeoff run.

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Table of Contents
1.1. THREE VIEW DRAWING ______________________________________________2
1.2. DESCRIPTIVE DATA _________________________________________________3
1.2.1. ENGINE ______________________________________________________________ 3
1.2.2. PROPELLER __________________________________________________________ 3
1.2.3. APPROVED FUEL TYPES AND GRADES_________________________________ 3
1.2.4. FUEL CAPACITY______________________________________________________ 3
1.2.5. APPROVED OIL GRADES ______________________________________________ 3
1.2.6. OIL CAPACITY _______________________________________________________ 3
1.2.7. TYRE INFLATION PRESSURES_________________________________________ 4
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GENERAL

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1.1. HREE VIEW DRAWING
Ground Turning Radius = 6.4 metres.
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GENERAL
GENERAL GENERAL
GENERAL

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1.2. DESCRIP IVE DA A
1.2.1.ENGINE
Manufacturer: Jabiru Aircraft Pty Ltd
Aero Engines Division
Type: 3300 Air Cooled
1.2.2.PROPELLER
Manufacturer: Jabiru Aircraft Pty Ltd
Type: Fixed Pitch Wooden Dwg No.
C000262-D60P43
Diameter: 60 inches (1524 mm)
Pitch: 53 inches (1346 mm)
1.2.3.APPROVED FUEL TYPES AND GRADES
100 LL or 100/130 grade aviation gasoline
1.2.4.FUEL CAPACITY
Total: 140.0 litres
Useable 138.0 litres
1.2.5.APPROVED OIL GRADES
Oils developed and branded for use in aircooled aircraft piston engines
(eg Aeroshell 100 plus)
In cold climates
Aero Oil W Multigrade 15W- 50
Or equivalent Lubricant Complying with,
MIL-L-22851C, or
Lycoming Spec301F, or
Teledyne Continental Spec MHF-24B
1.2.6.OIL CAPACITY
Sump capacity is 3.5 litres

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1.2.7.TYRE INFLATION PRESSURES
Standard Mains: 168 kpa (24 psi)
Nose: 84 - 105 kpa (12-15 psi)

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0
Section: 2LIMITATIONS
Table of Contents
Table of Contents ___________________________________________________________1
2.1. INTRODUCTI0N _______________________________________________________2
2.2. TYPE OF OPERATION__________________________________________________2
2.3. AIRSPEED LIMITATIONS_______________________________________________2
2.4. WEIGHTS and LOADING________________________________________________3
2.5. CENTRE OF GRAVITY LIMITS __________________________________________3
2.6. POWERPLANT LIMITATIONS ___________________________________________4
2.7. OTHER LIMITATIONS__________________________________________________4
2.7.1. AUTHORISED MANOEUVRES AND ASSOCIATED LIMITATIONS ____________ 4
2.7.2. SMOKING_______________________________________________________________ 4
2.7.3. MAXIMUM AIR TEMPERATURE FOR OPERATIONS _______________________ 5
2.7.4. FLIGHTS WITH DOORS REMOVED _______________________________________ 5
2.7.5. MAXIMUM PERMISSIBLE NUMBER OF OCCUPANTS ______________________ 5
2.7.6. MAXIMUM CROSSWIND VELOCITY ______________________________________ 5
2.8. PLACARDS____________________________________________________________6
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Section: 2LIMITATIONS
2.1. INTRODUCTI0N
Section 2 includes operating limitations, instrument markings and basic placards
necessary for the safe operation of the airplane, its engine, standard systems and
standard equipment. Observance of these operating limitations is required.
The aeroplane shall be operated so that the limitations and instructions included in
this section are observed.
2.2. TYPE OF OPERATION
VFR by Day
No aerobatics, including Spins.
2.3. AIRSPEED LIMITATIONS
Airspeed limitations and their operational significance are shown below.
SPEED KIAS REMARKS
V ne Never exceed speed 138 Do not exceed this speed in any operation.
V no Maximum structural cruising speed 120 Do not exceed this speed except in smooth air,
and then only with caution.
V a Manoeuvring speed 90 Do not make full or abrupt control movements
above this speed.
V fe Maximum flap extended speed 70 Do not exceed this speed with flaps down.
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Airspeed Indicator Markings and their operational significance are shown below.
MARKING KIAS
Value/Range
SIGNIFICANCE
White Arc 50 ! 70 Full flap operating range. Lower limit is max. weight
Vso in landing configuration. Upper limit is max. speed
permissible with flaps extended.
Green Arc 71 • 90 Normal operating range. Lower limit is Take-off Safety
speed. Upper limit is max. structural cruising speed.
Yellow Arc 91 • 138 Operations must be conducted with caution and only in
still air.
Red Line 138 Vne
2.4. WEIGHTS and LOADING
Maximum takeoff weight 700 kg
Maximum landing weight 700 kg
2.5. CENTRE OF GRAVITY LIMITS
Forward: 0-mm AFT of Datum up to and including 500kg
200-mm AFT of Datum at 700kg
Aft 282mm AFT of Datum
Datum : Wing Leading Edge
Leveling Means:
Longitudinal Spirit Level placed on Trim Lever Decal
Lateral Spirit Level placed across the fuselage forward of
the firewall on cowl location rubbers.
2.6. POWERPLANT LIMITATIONS
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Instrument Yellow Arc Green Arc Red Radial
Line/Arc
Tachometer 3200 RPM
Oil Temperature 50oC - 118Oc 118oC
Oil Pressure 80 kPa - 220 kPa 220 kPa - 525 kPa 80 kPa
Cylinder Head
Temperature
75oC - 175Oc
167oF - 347oF
175oC
347oF
Minimum Oil
Temperature for Takeoff
Needle must be seen to move off the stop
before Takeoff
Minimum Oil Pressure in Level Flight or climb 220 kPa
In Descent 80 kPa
Maximum Cylinder Head Temperature 175oC (347oF)
Maximum RPM for all operations 3200
Full Throttle Static RPM Not Above 3000
Not Under 2800
2.7. OTHER LIMITATIONS
2.7.1. AUTHORISED MANOEUVRES AND ASSOCIATED LIMITATIONS
Aerobatic manoeuvres, including spins, are not approved.
2.7.2. SMOKING
Prohibited.
2.7.3. MAXIMUM AIR TEMPERATURE FOR OPERATIONS
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40oc for takeoff at gross weight.
2.7.4. FLIGHTS WITH DOORS REMOVED
Prohibited.
2.7.5. MAXIMUM PERMISSIBLE NUMBER OF OCCUPANTS
Four (including Pilot).
2.7.6. MAXIMUM CROSSWIND VELOCITY
14 knots
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2.9. PLACARDS
Cockpit Placards General
Warning Placard
P/No5073794
WARNING
• Users of this aircraft do so at their own risk
• This aircraft must be flown in accordance with the Owners Manual
• Aerobatics Including spins are PROHIBITED
• Noise Level at Full Power exceeds 95 dB(A). Ear Protection Should be worn
A
IRCRAFT TYPE : JABIRU J400
Designed and Manufactured in Australia by
JABIRU AIRCRAFT Pty Ltd BUNDABERG QLD
Fitted on the rear Face of the Forward Wing Spar Carry-through Beam in the Cabin
Ceiling.
Owners Manual
P/No 5036194 FLIGHT/OWNERS MANUAL
Fitted to Inside of RH Door above the Door Pocket.
Door Open LHS
P/No5027094 OPEN
Fitted to the Outsides of LH Door Above the Door Catch Lever
Door Open RHS
P/No 5028094 OPEN
Fitted to the outside of RH Door Above the Door Catch Level
Door String Placard
P/No5026094 PULL TO OPEN
Fitted on Inside of both Doors Above Door Handle.
Fuel Contents
Appropriate to Fuel
Tank Fitted
Fitted on the Forward Side of the Fuel Tank
Baggage Label
P/No 5099184
Fitted on inside of fuselage on RHS with Line aligned with aft face of the fuel tank.
Loading Limitations
P/No 5098594
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LOADING LIMITATIONS
1. The maximum gross weight of the aircraft is not to
exceed 700 kg.
2. All baggage must be stowed either on the
passenger seat, or in the compartment behind
the rear of the seats
3. Pilots must use the Load and Trim Sheet given in
Section 6 of the Owner’s Manual to check the trim.
Fitted on inside of fuselage of RHS of cabin between Door and Rear Window.
P/No5098694-1
Cockpit Controls
Trim Position
P/No5024094 NOSE DOWN NEUTRAL TRIM NOSE UP BRAKE ON
Fitted on the Top of the Main Beam Beside the trim control
Fuel Tap Position
P/No 5223194
Fitted on the Main Beam in front of the Fuel SELECTOR Valve
Choke Cable
P/No5051094 CHOKE
PULL ON
Fitted at the base of the choke cable.
Carby Heat
P/No 5026194 CARB HEAT
PULL ON
Fitted at the base of the CARBY Heat Cable.
Note: This placard may be incorporated into the fascia of the instrument panel.
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