Jabiru J170-D 2020 Owner's manual

JP-FM-13
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Jabiru Aircraft
Model: J170-D
PILOT'S OPERATING HANDBOOK
JP-FM-13
Revision 4
28th February 2020
Airplane Registration Number:
Airplane Serial Number:
THIS DOCUMENT MUST BE CARRIED IN THE AIRCRAFT AT ALL TIMES
THIS AIRCRAFT MUST BE OPERATED IN ACCORDANCE WITH THE APPROVED
DATA AND LIMITATIONS CONTAINED IN THIS MANUAL AT ALL TIMES.
ANY PERSON FINDING THIS MANUAL IS REQUESTED TO RETURN IT TO JABIRU
AIRCRAFT

Jabiru Aircraft
Pilot Operating Handbook
Model J170-D
JP-FM-13
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Record of Manual Revisions
This manualis revised as acomplete document. All pages mustdisplay thesamerevisionnumber.
Revision Notes:
0
Initial Issue
1
Layout revised as per ASTM F2746 - 12
2
Omissions and Errors corrected
Amplified Emergency Procedure added
Minimum Take-off Oil temp corrected to be 40oC (104oF)
3
Note added to section 8.6
Oil spec changed to SAE J-1899 (MIL-L-22851 obsolete)
Add reference to JEM0002 in section 4.6.9
4
Fuel pressure max limit changed (section 2.7)
Add header tank fuel volume (section 6.1)
Extra Warning against oil & fuel additives (section 8.6)
𝑉
𝑂added to terminology (section 0.5)
Cruise power adjusted (Section 4.6.9)
Charging system procedures amplified (sections 3.3.5, 3.4.7 & 4.6.3).
PO Box (section 0.2)
Standards List (section 0.4)

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TABLE OF CONTENTS
0. INTRODUCTION ................................................................................. 0-7
0.1 PILOT’S OPERATING HANDBOOK.............................................. 0-7
0.2 SUPPORTING DOCUMENTATION............................................... 0-7
0.3 MANUFACTURER DETAILS......................................................... 0-8
0.4 STANDARDS LIST......................................................................... 0-8
0.5 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY................... 0-9
0.6 USE OF METRIC/IMPERIAL UNITS............................................ 0-14
0.7 WARNINGS, CAUTIONS &NOTES ............................................ 0-14
1. GENERAL INFORMATION............................................................... 1-15
1.1 LIGHT SPORT AIRCRAFT NOTIFICATION ................................ 1-15
1.2 ABOUT THE JABIRU J170-D....................................................... 1-16
1.3 OWNER/OPERATOR RESPONSIBILITES................................. 1-17
1.4 J170-D PERFORMANCE &SPECIFICATION SUMMARY.......... 1-17
2. LIMITATIONS.................................................................................... 2-18
2.1 AIRSPEED LIMITS....................................................................... 2-18
2.1.1 ASI Markings:......................................................................................2-18
2.2 AIRCRAFT SERVICE CEILING ................................................... 2-18
2.3 LIMIT LOAD FACTORS ............................................................... 2-19
2.4 FLIGHT OPERATION LIMITATIONS........................................... 2-19
2.5 FUEL............................................................................................ 2-19
2.6 FUEL GAUGES (WHERE EQUIPPED).............................................. 2-19
2.7 POWERPLANT LIMITATIONS..................................................... 2-19
2.8 CROSSWIND............................................................................... 2-20
2.9 OTHER CLIMATIC RESTRICTIONS ........................................... 2-20
2.10 KINDS OF OPERATION .............................................................. 2-20
2.11 POWER GENERATION SYSTEM LIMITATIONS........................ 2-20
2.12 OTHER LIMITATIONS ................................................................. 2-20
3. EMERGENCY PROCEDURES ......................................................... 3-21
3.1 AIRSPEEDS FOR EMERGENCY OPERATIONS........................ 3-21
3.2 CARBURETTOR ICING............................................................... 3-22
3.3 EMERGENCY PROCEDURES CHECK LISTS ........................... 3-23
3.3.1 Engine Failures....................................................................................3-23
3.3.2 Airstart & Limitations..........................................................................3-24
3.3.3 Forced Landings..................................................................................3-25
3.3.4 Engine Fires On Ground......................................................................3-25
3.3.5 Other Emergencies...............................................................................3-27

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3.4 AMPLIFIED EMERGENCY PROCEDURES.................................3-31
3.4.1 Fuel Gauges / Low Level warning Light (where equipped) ................ 3-31
3.4.2 Engine Failure..................................................................................... 3-31
3.4.3 Forced Landings ................................................................................. 3-31
3.4.4 Ditching............................................................................................... 3-32
3.4.5 Fires .................................................................................................... 3-32
3.4.6 Rough Engine/Loss of Power .............................................................. 3-32
3.4.7 Electrical Systems Malfunctions.......................................................... 3-33
4. NORMAL PROCEDURES..................................................................4-34
4.1 GENERAL.....................................................................................4-34
4.2 SPEEDS FOR NORMAL OPERATION.........................................4-34
4.3 BEST ANGLE OF CLIMB SPEED.................................................4-34
4.4 BEST RATE OF CLIMB SPEED....................................................4-34
4.5 PREFLIGHT INSPECTION...........................................................4-35
NORMAL PROCEDURES CHECK LISTS................................................4-38
4.5.1 Before Starting Engine........................................................................ 4-38
4.5.2 Starting Engine - Cold......................................................................... 4-38
4.5.3 Taxiing................................................................................................. 4-38
4.5.4 Before Take-Off................................................................................... 4-39
4.5.5 Take-Off............................................................................................... 4-39
4.5.6 Initial Climb ........................................................................................ 4-39
4.5.7 Cruise.................................................................................................. 4-40
4.5.8 Descent................................................................................................ 4-40
4.5.9 Before Landing (and flight below 1000ft AGL)................................... 4-40
4.5.10 Normal Landing............................................................................... 4-40
4.5.11 Baulked Landing .............................................................................. 4-40
4.5.12 After Landing/Securing.................................................................... 4-40
4.6 AMPLIFIED PROCEDURES.........................................................4-41
4.6.1 Preflight Inspection............................................................................. 4-41
4.6.2 Electric Fuel Gauges (where equipped):............................................. 4-41
4.6.3 Starting Engine.................................................................................... 4-41
4.6.4 Taxiing................................................................................................. 4-42
4.6.5 Engine Management –Ground Running............................................. 4-42
4.6.6 ................................................................................................................. 4-42
4.6.7 Take-Off............................................................................................... 4-43
4.6.8 Climb................................................................................................... 4-43
4.6.9 Cruise.................................................................................................. 4-43
4.6.10 Stalls................................................................................................. 4-43
4.6.11 Approach and Landing..................................................................... 4-44
4.6.12 Cross Wind Landing......................................................................... 4-44

Jabiru Aircraft
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4.6.13 Baulked Landing...............................................................................4-44
4.6.14 Flight Over Water.............................................................................4-44
4.7 ADVANCED PROCEDURES............................................................... 4-44
4.7.1 Short Field Take-Off ............................................................................4-45
4.7.2 Short Field Landing.............................................................................4-46
4.7.3 Soft Field Take-Off...............................................................................4-46
4.7.4 Soft Field Landing................................................................................4-47
4.7.5 Crosswind Take-Off .............................................................................4-48
4.7.6 Crosswind Landing –“Wing Low” Method ........................................4-48
4.7.7 Crosswind Landing –“Crab” Method.................................................4-49
4.7.8 S-Turns.................................................................................................4-50
4.7.9 Side Slips..............................................................................................4-50
5. PERFORMANCE............................................................................... 5-51
5.1 TAKE OFF AND LANDING DISTANCES..................................... 5-51
5.2 RATE OF CLIMB.......................................................................... 5-51
5.3 CRUISE SPEEDS /RPM /FUEL CONSUMPTION...................... 5-51
5.4 AIRSPEED INDICATOR SYSTEM CALIBRATION ................................... 5-52
6. WEIGHT AND BALANCE INFORMATION....................................... 6-52
6.1 CG RANGE .................................................................................. 6-52
6.2 BAGGAGE ZONES ........................................................................... 6-54
6.3 MINIMUM EQUIPMENT LIST ...................................................... 6-55
6.4 AIRCRAFT WEIGHT DATA.......................................................... 6-57
6.5 TRIM SHEETS ............................................................................. 6-60
6.5.1 Index Units...........................................................................................6-60
6.5.2 Calculate Aircraft Weights...................................................................6-60
6.5.3 Calculating the Operating CG Locations ............................................6-61
6.5.4 Allowable Loading Conditions.............................................................6-61
7. DESCRIPTION OF AIRPLANE AND SYSTEMS.............................. 7-64
7.1 GENERAL.................................................................................... 7-64
7.2 AIRFRAME................................................................................... 7-65
7.3 FLIGHT CONTROLS.................................................................... 7-65
7.4 INSTRUMENT PANEL................................................................. 7-65
7.5 FLIGHT INSTRUMENTS.............................................................. 7-66
7.5.1 Powerplant Instrument Markings ........................................................7-66
7.5.2 ASI markings........................................................................................7-67
7.5.3 EFIS & EMS LIMITATIONS DISPLAY ...............................................7-67
7.5.4 Required EFIS limitation displays:......................................................7-67
7.5.5 Required EMS Displays:......................................................................7-67

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7.6 ENGINE...........................................................................................7-67
7.7 PROPELLER ....................................................................................7-68
7.7.1 Jabiru Fixed Pitch Wooden Propeller................................................. 7-68
7.7.2 Jabiru Fixed Pitch Composite Scimitar Propeller .............................. 7-68
7.8 PLACARDS...................................................................................7-69
7.8.1 Cockpit Placards General................................................................... 7-69
7.8.2 Cockpit Controls ................................................................................. 7-71
7.8.3 External Fuselage ............................................................................... 7-72
8. HANDLING AND SERVICING ...........................................................8-74
8.1 INTRODUCTION...........................................................................8-74
8.2 GROUND HANDLING –TAXIING.................................................8-74
8.3 TOWING INSTRUCTIONS ...........................................................8-75
8.4 SECURING THE AIRCRAFT................................................................8-75
8.4.1 TIE-DOWN INSTRUCTIONS.............................................................. 8-75
8.4.2 Control Locks...................................................................................... 8-75
8.4.3 Security................................................................................................ 8-75
8.5 SERVICING ..................................................................................8-76
8.5.1 Fuelling ............................................................................................... 8-76
8.5.2 Fuelling –Alcohol Content Test.......................................................... 8-77
8.5.3 Engine Oil ........................................................................................... 8-77
8.6 APPROVED FUEL GRADES &SPECIFICATIONS......................8-78
8.6.1 Fuel Containing Alcohol..................................................................... 8-79
8.7 APPROVED OIL GRADES &SPECIFICATIONS .........................8-79
8.7.1 Engine Oil Viscosity Grade:................................................................ 8-79
8.8 BRAKES........................................................................................8-80
8.9 CLEANING &CARE......................................................................8-80
9. SUPPLEMENTS.................................................................................9-81
9.1 FLIGHT TRAINING SUPPLMENT ................................................9-81
9.2 INFORMATION FOR THE OWNER..............................................9-82
9.2.1 IMPROVEMENTS OR CORRECTIONS ............................................. 9-82
9.2.2 CONTINUED OPERATIONAL SAFETY REPORTING...................... 9-83
9.2.3 OWNER CHANGE OF ADDRESS NOTICE....................................... 9-83
9.3 SUPPLEMENTS ...........................................................................9-84
9.4 LOG OF SUPPLEMENTS –JABIRU AIRCRAFT SUPPLEMENTS..9-
84

Jabiru Aircraft
Pilot Operating Handbook
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0. INTRODUCTION
0.1 PILOT’S OPERATING HANDBOOK
The POH handbook consists of the following:
Basic POH
The basic POH provides all the information, procedures and limitations required to operate the
aircraft as a Light Sport Aircraft. This basic POH is applicable to all Jabiru J170-D Aircraft.
The operating procedures presented herein are the result of Jabiru Aircraft’s knowledge and
experience gained up to the date of issue of this handbook. The handbook may be used for
operational purposes only if kept in a fully amended state. It contains all the information considered
necessary to safely operate the aircraft.
The operator must be thoroughly familiar with the aircraft and the contents of this handbook before
initial operation. Thereafter the handbook should be reviewed periodically to enable the operator
to maintain the highest level of familiarity with the aircraft, itscontrols and recommended operating
procedures.
This POH also includes the information required of the Flight Training Supplement: there is no
separate FTS for the J170-D.
Supplements
Self contained supplements are provided in Section 9 of the POH to provide details andprocedures
associated with the fitment of specified optional and special purpose equipment. Supplements are
specific to the particular aircraft S/No. displayed on their title page.
Amendments
This manual is revised as a complete document. When a new issue of the manual becomes
available operators must transfer the aircraft-specific data (such as aircraft weight and balance
information and supplements) to the new manual. The old manual must not be used for further
operation of the aircraft.
Operators must then familiarise themselves with the new revision of the manual. Those sections
of the manual which have been revised are shown with red text.
0.2 SUPPORTING DOCUMENTATION
The following manuals are required for correct operation & maintenance ofthe Jabiru J170-D. The
current revisions are available free of charge from the Jabiru Aircraft website www.jabiru.net.au :
- Pilot’s Operating Handbook
- Aircraft Technical Manual (incorporating Propeller Maintenance Manual)
- Engine Maintenance Manual
- Engine Overhaul Manual

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In addition, the operator and maintainer must be aware of all current supplemental service
information issued by Jabiru Aircraft –again, the latest revisions are available from the Jabiru
Aircraft website. These documents include:
- Service Bulletins
- LSA Safety Directives
- Service Letters
Finally, operators and maintainers must be aware of any requirements issued by Airworthiness
Authorities and available from their respective web sites:
- Airworthiness Directives issued by the Civil Aviation Safety Authority
- Recreational Airworthiness Notice issued by Recreational Aviation Australia
0.3 MANUFACTURER DETAILS
Jabiru Aircraft P/L
PO Box 5792
Bundaberg West,
QLD 4670
Phone: [phone]
Fax: [phone]
Email: [email protected]t.au
Street Address: Jabiru Aircraft
5 Squadron Drive
Hinkler Airport,
Bundaberg
QLD 4670
0.4 STANDARDS LIST
Design & Performance The Jabiru J170-D has been designed to comply with the
requirements of ASTM F224.
Quality Assurance The Jabiru J170-D has been constructed under a Quality System
meeting the requirements of ASTM F2279.
Continued Airworthiness The continued airworthiness of the J170-D is monitored by Jabiru
Aircraft P/L in accordance with the requirements of ASTM F3198.
POH This POH has been prepared to comply with the requirements of
ASTM F2746.

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0.5 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
AAmpere
AGL Above Ground Level
AMSL Above Mean Sea Level
AVGAS Aviation Gasoline
BHP Brake Horse Power
CASA Civil Aviation Safety Authority (Australia)
CAO Civil Aviation Order (Australia)
CAR Civil Aviation Regulation (Australia)
°CDegrees Celsius
CHT Cylinder Head Temperature
cm Centimetre, centimetres
DC Direct Current
FAA Federal Aviation Administration (USA)
°FDegrees Fahrenheit
FAR Federal Aviation Regulation (USA)
FTS Flight Training Supplement
ft Foot, feet
ft/min Feet per minute
gAcceleration due to gravity
Gal Gallon
hPa Hectopascal, hectopascals
HF High Frequency
ICAO International Civil Aviation Organisation
IFR Instrument Flight Rules
IMC Instrument Meteorological Conditions
in Inch, inches
in Hg Inches of mercury
in lbs Inch pounds
ISA International Standard Atmosphere
kg Kilogram
kg/l Kilogram per litre
kHz Kilohertz
kts, K Knots
kPa Kilopascals
kW Kilowatt, kilowatts
lLitre, litres
lb Pound, pounds
LH Left hand

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LHS Left hand side
mMetre
m2Square metre
m3Cubic metre
mA Milli ampere
MAC Mean Aerodynamic Chord
max Maximum
MHz Megahertz
mm Millimetre
min Minimum or minute
MOGAS Automotive Fuel
nm Nautical mile, nautical miles
OAT Outside Air Temperature
PAX Passenger
POH Pilots Operating Handbook
PROP Propeller
psi Pounds per square inch
QTY Quantity
qts Quarts
RH Right Hand
RHS Right Hand Side
RON Fuel Octane Rating Scale (Research Octane Number)
RPM Revolutions per minute
SAE Society of Automotive Engineers
sec Seconds
SQ Square
STBY Standby
TBO Time between overhauls
T/O Take Off
U/S Unserviceable
USG US Gallon
US Gal US Gallon
VVolts
VFR Visual Flight Rules
VHF Very High Frequency
VMC Visual Meteorological Conditions
General Airspeed Terminology and Symbols

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•CAS Calibrated Airspeed: the indicated speed of an aircraft corrected for position
and instrument error. Calibrated airspeed is equal to true airspeed in standard
atmosphere at sea level.
•KCAS: Calibrated Airspeed expressed in knots.
•IAS Indicated Airspeed: the speed of an aircraft as shown on the airspeed
indicator. IAS values in this manual assume zero instrument error.
•KIAS Indicated Airspeed expressed in knots.
•TAS True Air Speed: the airspeed of an aircraft relative to the undisturbed air
through which it passes.
•T.O.S.S Take-Off Safety Speed: the airspeed chosen to ensure that adequate control
will exist under all conditions, including turbulence and sudden and complete
engine failure during the climb after take-off. It is the speed required at 50
feet.
•VAManoeuvring Speed: the maximum speed at which application of full available
aerodynamic control will not damage or overstress the aircraft.
•VFE Maximum Flap Extended Speed: the highest speed permissible with wing
flaps in a prescribed extended position.
•VO Operating Manoeuvring Speed: the speed that an aircraft will stall in a nose-
up pitching manoeuvre before exceeding structural limits. VOcannot exceed
𝑉
𝑠√𝑛.
•VNE Never Exceed Speed: the limiting airspeed that may not be exceeded at any
time.
•VCMaximum Structural Cruising Speed: the speed that should not be exceeded
except in smooth air and then only with caution.
•VSStalling Speed: or the minimum steady flight speed at which the aircraft is
controllable.
•VSO Stalling Speed: or the minimum steady flight speed at which the aircraft is
controllable in the landing configuration.
•VXBest Angle-of-Climb Speed: the airspeed which delivers the greatest gain of
altitude in the shortest possible horizontal distance.
•VYBest Rate-of-Climb Speed: the airspeed which delivers the greatest gain in
altitude in the shortest possible time.
Meteorological Terminology
•OAT –Outside Air Temperature –the outside free air static temperature.

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•Airfield Pressure Height –The height registered at the surface of an aerodrome by an
altimeter with the pressure sub-scale set to 1013 hPa (29.92 inches Hg).
•Pressure Altitude –Altitude measured from standard sea-level pressure (1013 hPa/29.92
inches Hg) by a pressure or barometric altimeter corrected for position and instrument error.
•Indicated Pressure Altitude –the altitude actually read from an altimeter when the pressure
barometric sub-scale has been set to 1013 hPa (29.92 inches Hg).
•QNH –The local pressure setting that if set on the subscale of an altimeter will cause the
altimeter to indicate local altitude above mean sea level.
•Wind –The wind velocities to be used as variables on aircraft performance are to be
understood as the headwind or tail wind components of the reported winds.
Aircraft Performance and Flight Planning Terminology
•Climb Gradient –The ratio of the change in height during a climb, to the horizontal distance
travelled.
•Demonstrated Crosswind Component –The crosswind component, during take-off and
landing, for which adequate control of aircraft was actually demonstrated during certification
tests.
Weight and Balance Terminology
•Datum –An imaginary vertical plane from which all horizontal distances are measured for
balance purposes.
•Station –A location along the aircraft fuselage usually given in terms of distance from the
reference datum.
•Arm –The horizontal distance from the reference datum to the centre of gravity (C of G) of
an item.
•Moment –The product of the weight of an item multiplied by its arm.
•Index Unit –Moment divided by a constant. Used to simplify balance calculations by
reducing the number of digits.
•Centre of Gravity (C of G) –The point at which an aircraft would balance if suspended. The
distance from the C of G to the reference datum can be found by dividing the total moment
by the total weight of the aircraft.
•C of G Arm –The arm obtained by adding the aircraft's individual moments and dividing the
sum by the total weight.
•C of G Limits –The extreme centre of gravity locations within which the aircraft must be
operated at a given weight.

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•Useable Fuel –The quantity of fuel available for flight planning purposes.
•Unusable Fuel –The quantity of fuel (determined under adverse fuel flow conditions) that
is not available for flight.
•Empty Weight –Weight of aircraft with unusable fuel and full oil.
•Useful Load –Difference between take-off weight, and basic empty weight.
•Maximum Take-Off Weight –Maximum weight approved for take-off.
•Maximum Landing Weight –Maximum weight approved for the landing.
•Header Tank –Fuel tank plumbed between the wing tanks and the engine. Also known as
Collector Tank or Sump Tank.

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0.6 USE OF METRIC/IMPERIAL UNITS
This POH uses the metric system as the basic system of measurement. Where common usage
or available instrumentation refer to the Imperial/US unit system, both units are quoted. The
following conversion factors are presented as a ready referencetothe conversion factors that have
been used in this manual as well as supplying some others that may be found useful.
1 Pound (lb) = 0.4536 Kilogram (kg)
1 Pound per sq in (psi) = 6.895 Kilopascal (kPa)
1 Inch (in) = 25.4 Millimetres (mm)
1 Foot (ft) = 0.3048 Metre (m)
1 Statute mile = 1.609 Kilometres (km)
1 Nautical mile (NM) = 1.852 Kilometres (km)
1 Millibar (mb) = 1 Hectopascal (hPa)
1 Millibar (mb) = 0.1 Kilopascal (kPa)
1 Imperial gallon = 4.546 Litres (l)
1 US gallon = 3.785 Litres (l)
1 US quart = 0.946 Litre (l)
1 Cubic foot (ft3) = 28.317 Litres (l)
1 Acre = 0.4047 Hectares
1 Degree Fahrenheit (F) = [1.8 x C]+32
1 Inch Pound (in lb) = 0.113 Newton Metres (Nm)
1 Foot Pound (ft lb) = 1.356 Newton Metres (Nm)
0.7 WARNINGS, CAUTIONS & NOTES
Definitions used in the POH such as WARNING, CAUTION, NOTE are employed in the following
context: WARNING
Operating procedures, techniques, etc. which if not followed correctly, may result in personal
injury or death.
CAUTION
Operating procedures, techniques, etc. which if not strictly observed, may result in damage to the
aircraft or to its installed equipment.
NOTE
Operating procedures, techniques, etc. which it is considered essential to highlight.

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1. GENERAL INFORMATION
1.1 LIGHT SPORT AIRCRAFT NOTIFICATION
There are inherent risks in the participation in recreational aviation aircraft. Operators and
passengers of recreational aviation aircraft, by participation, accept the risks inherent in such
participation of which the ordinary prudent person is or should be aware. Pilots and passengers
have a duty to exercise good judgment and act in a responsible manner while using the aircraft
and to obey all oral or written warnings, or both, prior to or during use of the aircraft, or both.
WARNING:
THIS AIRCRAFT WAS MANUFACTURED IN ACCORDANCE WITH LIGHT SPORT
AIRCRAFT AIRWORTHINESS STANDARDS AND DOES NOT CONFORM TO STANDARD
CATEGORY AIRWORTHINESS REQUIREMENTS.
Jabiru Aircraft Pty Ltd has devoted significant resources and testing to develop the Jabiru
J170-D aircraft. The Jabiru J170-D is designed to be operated and maintained only in strict
accordance with its supporting documentation –consisting of Pilot’s Operating Handbook,
Aircraft Technical Manual (Including Maintenance Manual), Engine Maintenance Manual,
Propeller Maintenance Manual, Jabiru Australia Service Bulletins, Service Letters and any
other documents produced by Jabiru Aircraft Australia or the appropriate regulatory
authorities.
Any variation in procedure or failure to operate or maintain the aircraft according to the
supporting documentation may cause damage or harm to the aircraft, its parts, or
components and may lead to injury or death. Any such actions may render the aircraft un-
airworthy and will void any warranty issued by Jabiru.
Any variation to the aircraft of any kind, including alteration to any component at all,
whether replacement, relocation, modification or otherwise which is not strictly in
accordance with these documents may lead to dramatic changes in the performance of the
aircraft, may cause damage or harm to other parts of the aircraft and may lead to injury or
death. Jabiru Aircraft Pty Ltd does not support any modifications to the aircraft, its parts,
or components. Any such actions may render the aircraft un-airworthy and will void any
warranty issued by Jabiru.
Maintenance cannot be supervised by the manufacturer. Maintenance requires extreme
cleanliness, exact parts, precise workmanship and proper consumables. It is your
responsibility to ensure absolute attention to detail no matter who may become involved in
work on this aircraft. Your safety, your life and your passenger’s lives rely on precise and
accurate following of the maintenance documentation for this aircraft.

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1.2 ABOUT THE JABIRU J170-D
Jabiru Aircraft have been built in Bundaberg, Australia since the early 1990’s. The original was a
small 2 seat aircraft powered by a 2-stroke engine; it had limited range, basic equipment and little
room to spare in the cabin. But this aircraft introduced the Jabiru ideal to the world –an aircraft
which was light and efficient with good handling, good performance and excellent occupant
protection. An aircraft which met all these goals while using modern technology to be cost effective
to own and operate and to introduce newcomers to aviation –people who always thought that
aviation was beyond their reach. Since the time of those first aircraft, Jabiru Aircraft have evolved
dramatically. The current Jabiru models are all far more powerful, spacious and better equipped
than their ancestor while still meeting the Jabiru Ideal.
The Jabiru J170-D was developed with hot climate flying schools in mind. It combines the compact
inexpensive airframe of a J160 with the large wing and elevator surfaces of the J230. This gives it
a very low stall speed making it one of the safest and easiest aircraft for student pilots to learn to
land. It is forgiving of learner-pilot mistakes and the side-by-side seating makes the instructor’s job
easy. The aircraft makes an excellent cross-country machine resulting from the high aspect ratio
wing and very low parasitic drag, combined with two large wing tanks gives the J170-D an
endurance exceeding 8 hours and cruise speeds of 100knots (TAS). The powerful engine is
smooth and quiet so that the crew can fly for hours without fatigue from noise and vibration.
On the ground the J170-D is also an excellent performer –The simple robust design allows
maintenance to be carried out quickly and easily to get the aircraft back into the air as soon as
possible. The same Jabiru 2200 engine which provides powerful performance in the air is also
light, simple, easy to maintain and so quiet that people living near the airport barely hear it. The
composite construction allows the aircraft to be both light and very strong –with the J170-D being
designed to an ultimate factor of around +8g / -4g. The fibreglass structure won’t rust or corrode,
has an almost infinite fatigue life and like all Jabirus, the J170-D has been designed with a very
strong cabin structure to provide a safety cell for its crew.
Today’s J170-D is the latest design of an aircraft model which has been a popular choice with pilots
for many years. The design is thoroughly proven and thoroughly tested –both by Jabiru test
pilots and demanding customers all over the world. It can be extensively customised and thanks
to the wide range of interior options, instrument systems and other optional extras every Jabiru
J170-D is unique. Most importantly, the J170-D still embodies the original Jabiru Ideal and
continues to show people who never thought they could have an aircraft of their own that anything
is possible.

Jabiru Aircraft
Pilot Operating Handbook
Model J170-D
JP-FM-13
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1.3 OWNER/OPERATOR RESPONSIBILITES
The following responsibilities for the owner/operator of a LSA listed are prescribed in the
ASTM standard F2295:
•Each owner/operator of a LSA shall read and comply with the maintenance and
continued airworthiness information and instructions provided by the manufacturer.
•Each owner/operator of a LSA shall be responsible for providing the manufacturer with
current contact information where the manufacturer may send the owner/operator
supplemental notification bulletins.
•The owner/operator of a LSA shall be responsible for notifying the manufacturer of any
safety of flight issue or significant service difficulty upon discovery.
•The owner/operator of a LSA shall be responsible for complying with all manufacturer
issued notices of corrective action and for complying with all applicable aviation
authority regulations in regard to maintaining the airworthiness of the LSA.
•An owner of a LSA shall ensure that any needed corrective action be completed as
specified in a notice, or by the next scheduled annual inspection.
•Should an owner/operator not comply with any mandatory service requirement, the
LSA shall be considered not in compliance with applicable ASTM standards and may
be subject to regulatory action by the presiding aviation authority.
1.4 J170-D PERFORMANCE & SPECIFICATION SUMMARY
Gross Weight
600kg (1323 lb)
Top Speed at Sea Level
120 KCAS (at full power)
Cruise Speed at Sea level
90 KCAS (at 2800 rpm)
Full Fuel Range1
800nm at 2800 rpm, 5000’ ASL (if achieving 15 lt/hr fuel
consumption)
Rate of Climb at Sea Level2
500 fpm (VY)
450 fpm (VX)
Take-Off Distance
600 m
Landing Distance
513 m
Stall Speed Clean
45 KCAS
Stall Speed Flaps Full Down
40 KCAS
Fuel Capacity
140L (37 USgal) Total Capacity
135L (35.6 USgal) Usable
Approved Fuels
AVGAS 100LL, AVGAS 100/130 or MOGAS with RON of 95 or
higher
Maximum Engine Power
80 hp @ 3300 RPM.
Refer to the main body of this handbook below for more information.
1
Range with 45 minute reserve at stated power setting
2
At Gross Weight, ICAO Standard Atmosphere

Jabiru Aircraft
Pilot Operating Handbook
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2. LIMITATIONS
2.1 AIRSPEED LIMITS
SPEED
KIAS
ASI
MARKINGS
REMARKS
Design Manoeuvring Speed (VA)
94
-
Do not make full or abrupt
control movements above
this speed.
Operating Manoeuvring Speed at
MTOW (VO MTOW)*
94
-
Do not make full or abrupt
control movements above
this speed at MTOW
Operating Manoeuvring Speed at
Minimum weight (VOMIN)**
68
-
Do not make full or abrupt
control movements above
this speed at Minimum
weight
Never Exceed Speed (VNE)
140
Red Line at upper
end of yellow arc
Do not exceed this speed in
any operation.
Max Structural Cruising Speed (VC)
112
Upper end of
green arc/start of
yellow arc
Do not exceed this speed
except in smooth air and
then with caution.
Maximum Flap Extension Speed (VFE)
84
Upper end of
white arc
Do not exceed this speed
with the flaps deployed.
Stalling Speed, Clean (VS)
47
Lower end of
green arc
in Cruise Configuration
Stalling Speed, Full Flaps (VS0)
42
Lower end of
white arc
in Landing Configuration
*Operating Manoeuvring speed at ‘MTOW’ refers to maximum gross weight = 600kg (1323lb).
** Operating Manoeuvring speed at ‘Minimum weight’ is calculated based on typical light empty
weight (325kg), a single lightweight occupant (55kg) and 45 minutes reserve fuel (10kg) = 390kg
(860lb). Typical operating weight will usually always be much heavier.
Note: Refer to Section 5.4 for conversion to Calibrated Airspeed (KCAS)
2.1.1 ASI Markings:
White Arc: Flap extended speed range (VS0 to VFE) –flapped stall speed to maximum
allowable with flaps deployed (42-84 KIAS)
Green Arc: Normal operating Speed range (47-112 KIAS)
Yellow Arc: Caution speed range –Do not exceed this speed except in smooth air and
then with caution. (112-140 KIAS)
Red Line: Do not exceed this speed in any operation (140 KIAS).
2.2 AIRCRAFT SERVICE CEILING
10 000 feet ASL

Jabiru Aircraft
Pilot Operating Handbook
Model J170-D
JP-FM-13
Revision:
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2.3 LIMIT LOAD FACTORS
Flap Position
Speed
Positive
Negative
UP
UP
DOWN
VA
VNE
VFE
+ 4g
+ 4g
+ 2.0g
-2g
-2-g
0g
2.4 FLIGHT OPERATION LIMITATIONS
Manoeuvres in the course of normal flying are approved.
Stalls may be carried out at bank angles of up to 60°.
All aerobatic manoeuvres including spins are prohibited.
Flight Operations are limited to VMC (Visual Meteorological Conditions).
Flight Operations in IMC (Instrument Meteorological Conditions) are prohibited.
2.5 FUEL
Total Capacity: 140L (37 USgal) Total (2 OFF 67.5L Wing Tanks + 5L Header
Tank)
Usable Capacity: 135L (35.6 USgal) Useable
Grade: Avgas 100LL, Avgas 100/130 or MOGAS with RON of 95 or
higher. See Section 8.6
Max zero wing fuel weight: Equal to gross weight, 600kg (1323 lb)
(WZWF)
2.6 FUEL GAUGES (where equipped)
Fuel pickups are in wing roots. Care must be taken to maintain balanced flight at low fuel levels to
ensure that fuel can be drawn from both tanks. If the aircraft is flown for extended periods in an
unbalanced condition, it is possible to fully drain one tank while there remains fuel in the other.
2.7 POWERPLANT LIMITATIONS
POWER
RPM
Maximum
Temperatures
Fuel Pressure
Limits
Oil Pressure
Limits
Cyl
Head
Oil
Min
Max
Min
Max
Absolute
Limits
Maximum
Take-Off
(80 BHP)
3300
200 °C
(392°F)
(Note #1)
118°C
(244°F)
5 kPa
(0.75psi)
35 kPa
(5.0psi)
220 kPa
(31 psi)
525 kPa
(76psi)
Continuous
Limits
Maximum
Cont
(80 BHP)
3300
180°C
(356°F)
100°C
(212°F)
5 kPa
(0.75psi)
35 kPa
(5.0psi)
220 kPa
(31 psi)
525 kPa
(76 psi)
Limits For
Ground
Running
N/A
N/A
180°C
(356°F)
(Note #2)
100°C
(212°F)
(Note #2)
5 kPa
(0.75psi)
35 kPa
(5.0psi)
80 kPa
(11 psi)
525 kPa
(76 psi)
Note #1 Time with CHT at between 180°C and 200°C is not to exceed 5 Minutes

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JP-FM-13
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Note #2 If temperature limits are reached, shut the engine down or cool it by pointing the
aircraft into wind.
Other limits are as follows:
•Minimum oil pressure at idle: 80 kPa (11 psi)
•Maximum oil pressure at start: 525 kPa (76 psi)
2.8 CROSSWIND
The maximum allowable crosswind velocity is dependent on many factors including:
- Aircraft limitations
- Pilot capability.
- Ground conditions –i.e. turbulence from structures or trees
- Wind state –i.e. steady wind or gusting / thermal conditions.
With average pilot technique, steady, direct crosswinds of up to 14 knots can be handled with
safety.
2.9 OTHER CLIMATIC RESTRICTIONS
Maximum Ambient Operating Temperature 38°C (100°F)
Flight into known icing conditions Prohibited
2.10 KINDS OF OPERATION
The standard J170-D, as detailed within this POH, is approved for Day VFR Operations only
2.11 POWER GENERATION SYSTEM LIMITATIONS
When the engine is turning at approximately 2000 RPM and above the alternator produces
sufficient power for all lights to be run continuously. However, belowthis RPM the alternator cannot
produce this power output and power must be drawn from the battery if all electrical systems are
running. To reduce the load on the alternator, Jabiru Aircraft recommend only using the Landing
Light for takeoff and landing –turning it off during normal cruise operations and wherever safe
while taxiing.
2.12 OTHER LIMITATIONS
•Smoking is prohibited.
•In-cabin noise levels exceed 95db. Hearing protection must be worn.