Jabiru Aircraft Model J120

Jabiru Aircraft
Model J120-C
PILOT'S OPERATING HANDBOOK
Revision 0
THIS DOCUMENT MUST BE CARRIED IN THE AIRCRAFT AT ALL TIMES
Jabiru Aircraft
Pilot’s Operating Handbook
Model J120-C
AIRCRAFT PARTICULARS
THIS AIRCRAFT MUST BE OPERATED IN ACCORDANCE WITH THE APPROVED
DATA AND LIMITATIONS CONTAINED IN THIS MANUAL AT ALL TIMES.
Registration Marks:
Manufacturer:
Aircraft Serial Number:
Certification Categories:
____________
Jabiru Aircraft Pty Ltd
_________________
Light Sport Aircraft
Any person finding this Manual is requested to return it to Jabiru Aircraft P/L.
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Jabiru Aircraft
Pilot’s Operating Handbook
Model J120-C
AMENDMENT RECORD SHEET
Amendment
Date
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Affected
Sections
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Date
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Signature
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Jabiru Aircraft
Pilot’s Operating Handbook
Model J120-C
0.1
INTRODUCTION
This Operating Handbook has been prepared to comply with the requirements of ASTM F2245.
This Operating Handbook includes the information required of the Flight Training Supplement.
The basic handbook provides all the information, procedures and limitations required to
operate the aircraft as a Light Sport Aircraft. Information, procedures and limitations
relating specifically to other operations are provided in the appropriate supplement.
The operating procedures presented herein are the result of Jabiru Aircraft’s knowledge and
experience gained up to the date of issue or amendment of this handbook. The handbook is not
intended to be a guide for basic flight instruction or as a training manual. It 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, its controls and recommended
operating procedures.
0.2
PILOT’S OPERATING HANDBOOK (POH)
The handbook is valid only for the particular aircraft identified on the AIRCRAFT
PARTICULARS page, and unless subsequently amended, refers to the aircraft as originally
delivered from the factory. The handbook consists of the following:
Basic POH
The basic POH provides all required details of the standard aircraft and the procedures required
to operate it in the LSA category. Apart from the listing in Section Error! Reference source not
found., no other details of any optional equipment fitted at the factory will be found in the basic
POH. Refer to the relevant supplement.
Supplements
Self contained supplements are provided in SECTION Error! Reference source not found. of
the POH to provide details and procedures associated with the fitment of specified optional and
special purpose equipment.
Amendments
Any amendments to any page of the POH is to have an amendment date. All amendments are
to be incorporated as soon as possible after their receipt and details entered into the appropriate
amendment record sheet.
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Pilot’s Operating Handbook
Model J120-C
0.3
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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Pilot’s Operating Handbook
Model J120-C
0.4
THREE-VIEW DRAWING
Figure 1-1 Three View of the J120
Note: All dimensions in millimetres
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Pilot’s Operating Handbook
Model J120-C
0.5
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
0.5.1
General Symbols and Abbreviations
A
AGL
AMSL
AVGAS
BHP
CASA
CAO
CAR
°C
CHT
cm
DC
FAA
°F
FAR
ft
ft/min
g
Gal
hPa
HF
ICAO
IFR
IMC
in
in Hg
in lbs
ISA
kg
kg/l
kHz
kts, K
kPa
kW
l
lb
LH
LHS
m
m2
m3
mA
MAC
max
MHz
mm
min
MOGAS
nm
OAT
JP-FM-10
Ampere
Above Ground Level
Above Mean Sea Level
Aviation Gasoline
Brake Horse Power
Civil Aviation Safety Authority (Australia)
Civil Aviation Order (Australia)
Civil Aviation Regulation (Australia)
Degrees Celsius
Cylinder Head Temperature
Centimetre, centimetres
Direct Current
Federal Aviation Administration (USA)
Degrees Fahrenheit
Federal Aviation Regulation (USA)
Foot, feet
Feet per minute
Acceleration due to gravity
Gallon
Hectopascal, hectopascals
High Frequency
International Civil Aviation Organisation
Instrument Flight Rules
Instrument Meteorological Conditions
Inch, inches
Inches of mercury
Inch pounds
International Standard Atmosphere
Kilogram
Kilogram per litre
Kilohertz
Knots
Kilopascals
Kilowatt, kilowatts
Litre, litres
Pound, pounds
Left hand
Left hand side
Metre
Square metre
Cubic metre
Milli ampere
Mean Aerodynamic Chord
Maximum
Megahertz
Millimetre
Minimum or minute
Automotive Fuel
Nautical mile, nautical miles
Outside Air Temperature
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Pilot’s Operating Handbook
Model J120-C
PAX
POH
PROP
psi
QTY
qts
RH
RHS
RON
RPM
SAE
sec
SQ
STBY
TBO
T/O
U/S
USG
US Gal
V
VFR
VHF
VMC
0.5.2
Passenger
Pilots Operating Handbook
Propeller
Pounds per square inch
Quantity
Quarts
Right Hand
Right Hand Side
Fuel Octane Rating Scale (Research Octane Number)
Revolutions per minute
Society of Automotive Engineers
Seconds
Square
Standby
Time between overhauls
Take Off
Unserviceable
US Gallon
US Gallon
Volts
Visual Flight Rules
Very High Frequency
Visual Meteorological Conditions
General Airspeed Terminology and Symbols
•
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.
•
VA
Manoeuvring 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.
•
VNE
Never Exceed Speed: the limiting airspeed that may not be exceeded at any
time.
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Model J120-C
•
VC
Maximum Structural Cruising Speed: the speed that should not be exceeded
except in smooth air and then only with caution.
•
VS
Stalling 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.
•
VX
Best Angle-of-Climb Speed: the airspeed which delivers the greatest gain of
altitude in the shortest possible horizontal distance.
•
VY
Best Rate-of-Climb Speed: the airspeed which delivers the greatest gain in
altitude in the shortest possible time.
0.5.3
Meteorological Terminology
•
OAT – Outside Air Temperature – the outside free air static temperature.
•
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.
0.5.4
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.
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Pilot’s Operating Handbook
Model J120-C
0.5.5
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.
•
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.
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Pilot’s Operating Handbook
Model J120-C
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 reference to the conversion factors that
have been used in this manual as well as supplying some others that may be found useful.
1 Pound (lb)
1 Pound per sq in (psi)
1 Inch (in)
1 Foot (ft)
1 Statute mile
1 Nautical mile (NM)
1 Millibar (mb)
1 Millibar (mb)
1 Imperial gallon
1 US gallon
1 US quart
1 Cubic foot (ft3)
1 Acre
1 Degree Fahrenheit (ΕF)
1 Inch Pound (in lb)
1 Foot Pound (ft lb)
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=
=
=
=
=
=
=
=
=
=
=
=
=
=
=
=
0.4536 Kilogram (kg)
6.895 Kilopascal (kPa)
25.4 Millimetres (mm)
0.3048 Metre (m)
1.609 Kilometres (km)
1.852 Kilometres (km)
1 Hectopascal (hPa)
0.1 Kilopascal (kPa)
4.546 Litres (l)
3.785 Litres (l)
0.946 Litre (l)
28.317 Litres (l)
0.4047 Hectares
[1.8 x ΕC]+32
0.113 Newton Metres (Nm)
1.356 Newton Metres (Nm)
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Jabiru Aircraft
Pilot’s Operating Handbook
Model J120-C
TABLE OF CONTENTS
INTRODUCTION ............................................................................1-4
PILOT’S OPERATING HANDBOOK (POH)....................................1-4
WARNINGS, CAUTIONS & NOTES ...............................................1-5
THREE-VIEW DRAWING ...............................................................1-6
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY....................1-7
USE OF METRIC/IMPERIAL UNITS.............................................1-11
0.1
0.2
0.3
0.4
0.5
0.6
1
SECTION 1 - GENERAL ....................................................................1-14
1.1
1.2
1.3
1.4
2
MANUFACTURERS STATEMENT OF COMPLIANCE ................1-14
MANUFACTURER DETAILS ........................................................1-15
LIGHT SPORT AIRCRAFT NOTIFICATION .................................1-15
J120-C PERFORMANCE AND SPECIFICATION SUMMARY .....1-15
SECTION 2 – AIRPLANE & SYSTEMS DESCRIPTION...................2-16
2.1
2.2
2.3
2.4
2.5
3
ENGINE...........................................................................................2-16
PROPELLER ....................................................................................2-16
FUEL ..............................................................................................2-16
ENGINE OIL.....................................................................................2-16
CENTRE OF GRAVITY LIMITS ....................................................2-16
SECTION 3 – OPERATING LIMITATIONS .......................................3-19
3.1
3.2
3.3
3.4
3.5
3.6
3.7
3.8
3.9
3.10
3.11
3.12
4
KINDS OF OPERATION ...............................................................3-19
AIRSPEED LIMITATIONS ............................................................3-19
CROSSWIND....................................................................................3-19
AIRCRAFT SERVICE CEILING ............................................................3-19
LOAD FACTORS ..........................................................................3-19
PROHIBITED MANOEUVRES ..............................................................3-19
POWER PLANT LIMITATIONS ....................................................3-20
FUEL GRADE ...................................................................................3-20
POWER PLANT INSTRUMENT MARKINGS ...............................3-21
REQUIRED EFIS DISPLAYS........................................................3-21
OTHER LIMITATIONS ..................................................................3-21
PLACARDS...................................................................................3-21
SECTION 4 – WEIGHT & BALANCE INFORMATION .....................4-26
4.1
4.2
5
CENTRE OF GRAVITY LIMITS ....................................................4-26
TRIM SHEETS ..................................................................................4-29
SECTION 5 – PERFORMANCE ........................................................5-33
5.1
5.2
5.3
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TAKE OFF AND LANDING DISTANCES......................................5-33
RATE OF CLIMB...........................................................................5-33
CRUISE SPEEDS / RPM / FUEL CONSUMPTION ......................5-33
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Pilot’s Operating Handbook
Model J120-C
5.4
6
AIRSPEED INDICATOR SYSTEM CALIBRATION.................................... 5-34
SECTION 6 - EMERGENCY PROCEDURES ................................... 6-35
6.1
6.2
6.3
7
GENERAL .................................................................................... 6-35
AIRSPEEDS FOR EMERGENCY OPERATIONS........................ 6-35
EMERGENCY PROCEDURES CHECK LISTS............................ 6-35
SECTION 7 – NORMAL PROCEDURES.......................................... 7-40
7.1
7.2
7.3
7.4
GENERAL .................................................................................... 7-40
SPEEDS FOR NORMAL OPERATION ........................................ 7-40
PREFLIGHT INSPECTION .......................................................... 7-41
NORMAL PROCEDURES CHECK LISTS ................................... 7-44
8
SECTION 8 – GROUND HANDLING & SERVICING ....................... 8-47
8
SECTION 8 – GROUND HANDLING & SERVICING ....................... 8-47
8.1
8.2
8.3
9
FUEL ............................................................................................ 8-47
OIL................................................................................................ 8-48
BRAKES ....................................................................................... 8-48
SECTION 9 – SUPPLEMENTS ......................................................... 9-49
9.1
9.2
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INTRODUCTION.......................................................................... 9-49
SUPPLEMENT LOG – JABIRU AIRCRAFT SUPPLEMENTS ..... 9-50
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Pilot’s Operating Handbook
Model J120-C
1
SECTION 1 - GENERAL
1.1
MANUFACTURERS STATEMENT OF COMPLIANCE
INSERT COPY OF MANUFACTURERS STATEMENT OF COMPLIANCE
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Pilot’s Operating Handbook
Model J120-C
1.2
MANUFACTURER DETAILS
Jabiru Aircraft P/L
PO Box 5186
Bundaberg West,
QLD 4670
Phone: 07 4155 1778
Fax: 07 4155 2669
Email: info@jabiru.net.au
Street Address:
Jabiru Aircraft
Airport Drive, Hinkler Airport
Bundaberg
QLD 4670
1.3
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.
1.4
J120-C PERFORMANCE AND SPECIFICATION SUMMARY
Gross Weight
500kg (11102 lb)
Top Speed at Sea Level
120 KCAS
380 nm at 75% power
1
Full Fuel Range
450 nm at most efficient power setting
Rate of Climb at Sea Level2
500 fpm
Take-Off Distance
400 m
Landing Distance
300 m
Stall Speed Clean
49 KCAS
Stall Speed Flaps Full Down
45 KCAS
Fuel Capacity
64 L Useable
Approved Fuels
AVGAS or MOGAS with RON of 95 or higher.
Maximum Engine Power
85 hp @ 3300 RPM.
Refer to the main body of this handbook below for more information.
1
2
Range with 45 minute reserve at stated power setting
At Gross Weight, ICAO Standard Atmosphere
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Pilot’s Operating Handbook
Model J120-C
2
SECTION 2 – AIRPLANE & SYSTEMS DESCRIPTION
2.1
Engine
Manufacturer:
Jabiru Aircraft Pty Ltd
Model:
Jabiru 2200-B
2.2
Propeller
Manufacturer:
Jabiru Aircraft Pty Ltd
Model:
C000262-D60P42
Type:
Wooden, Fixed Pitch
Number of blades:
2
Diameter:
1524 mm (60 in)
Pitch
1067 mm (42 in)
Max RPM:
3300
2.3
Fuel
Capacity:
Grade:
64L Useable
Avgas 100LL
Avgas 100/130
MOGAS with minimum Octane Rating of 95 RON1 may be used.
Do not use fuel additives such as Octane Boosters.
Refer to Section 3 for additional details.
2.4
Engine Oil
Jabiru Aircraft approves lubricating oils of any brand name conforming to specifications MIL-L6082 for straight mineral oil and MIL-L-22851 for ashless dispersant oil.
Refer to Section Error! Reference source not found. for additional details.
2.5
CENTRE OF GRAVITY LIMITS
1601-mm (63.03”, 20%MAC) aft of datum up to & including
420 kg (926lb)
Forward Limit:
1661-mm (63.39”, 26.1%MAC) aft of datum at 500kg
(1190lb)
Linear variation between points.
Aft Limit
1695-mm (66.73”, 29.5%) aft of datum at all weights
Datum
1403mm fwd of RHS Wing Leading Edge
Levelling Means
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Pilot’s Operating Handbook
Model J120-C
Longitudinal
Spirit Level placed on the trim decal on the centre console.
Lateral
Spirit Level placed on the flap cross shaft.
Arms
Arm for Front Seat Station
1688-mm aft of datum
Arm for Baggage On Shelf
2280-mm aft of datum
Fuel Station
2280-mm aft of datum
Table 2.7
Refer to Section 4 for additional details
2.5.1
Minimum Equipment List
Opt.
Description
Code
Weight
Arm
kg (lb)
mm (in)
61kg
(135lb)
280mm
(11.02in)
0.5kg
(1.1lb)
1.7kg
(3.7lb)
0.6kg
(1.3lb)
280mm
(11.02in)
-60mm
(2.36in)
-60mm
(2.36in)
0.5kg
(1.1lb)
0.8kg
(1.8lb)
0.7kg
(1.5lb)
0.2kg
(0.4lb)
0.2kg
(0.4lb)
0.4kg
(0.9lb)
0.2kg
(0.4lb)
1110mm
(43.70in)
1110mm
(43.70in)
1110mm
(43.70in)
1110mm
(43.70in)
1110mm
(43.70in)
1110mm
(43.70in)
1110mm
(43.70in)
Firewall Fwd
Engine: Jabiru 2200. Includes starter, alternator,
carburettor, muffler, spark plugs, prop flange extension
and oil filter assembly
Oil Cooler (empty): P/No. PH4A015N
Propeller: P/No. C000242-60D42P
Spinner Assembly: 4A189A0D
Instruments
Airspeed Indicator
Altimeter
O
EFIS: Dynon EFIS-D10A
Oil Pressure Gauge
Oil Temperature Gauge
Tachometer
Cylinder Head Temperature
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Model J120-C
Opt.
Description
Code
Weight
Arm
kg (lb)
mm (in)
6.7kg
(14.8lb)
0.5kg
(1.1lb)
0.7kg
(1.5lb)
0.6kg
(1.3lb)
0.8kg
(1.8lb)
910mm
(35.83in)
1110mm
(43.70in)
1110mm
(43.70in)
1688mm
(66.46in)
1000mm
(39.37in)
0.1kg
(0.2lb)
1.0kg
(2.2lb)
1.5kg
(3.3lb)
1.5kg
(3.3lb)
0.4kg
(0.9lb)
0.4kg
(0.9lb))
0.1kg
(0.2lb)
2280mm
(89.76in)
1688mm
(66.46in)
304mm
(11.97in)
804mm
(31.65in)
-210mm
(-8.27in)
-266mm
(-10.47in)
1110mm
(43.70in)
Electrical Equipment
Battery (Odyssey PC625)
VHF COMM #1:
O
Transponder
Headsets
O
Ameri-King Altitude Encoder (AK-350)
Miscellaneous
Baggage Restraint Straps (Each)
Seat Covers Cloth:
O
Seat Covers Sheepskin
O
Tool Kit
Flight Manual
Compass
Door Pockets
Additions/Deletions
Table 2.11.2
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Pilot’s Operating Handbook
Model J120-C
3
SECTION 3 – OPERATING LIMITATIONS
3.1 KINDS OF OPERATION
The standard J120-C, as detailed within this POH, is approved for Day VFR Operations only.
3.2
AIRSPEED LIMITATIONS
The indicated airspeeds in the table below are based on airspeed calibration data from Section 5.
SPEED
KIAS
REMARKS
Max Manoeuvring Speed (VA)
103
Never Exceed Speed (VNE)
146
Max Structural Cruising Speed
(VC or VNO)
113
Do not make full or abrupt control
movements above this speed.
Do not exceed this speed in any
operation.
Do not exceed this speed except in
smooth air and then with caution.
Do not exceed this speed with the flaps
deployed.
Maximum Flap Extension Speed (VFE)
94
Stalling Speed (VS)
51
In cruise configuration
Stalling Speed (VS0)
47
In landing configuration
Table 2.2
Refer to Section 6 for Indicated Airspeed Limitations
3.3
Crosswind
The maximum allowable crosswind velocity is dependant on pilot capability as well as aircraft
limitations. With average pilot technique, direct crosswinds of 14 knots can be handled with
safety.
3.4
Aircraft Service Ceiling
10 000 feet ASL
3.5 LOAD FACTORS
Flap Position
Speed
Positive
UP
VA
+ 4g
Negative
-2g
UP
VNE
+ 4g
-2-g
DOWN
VFE
+ 2.0g
0g
3.6 Prohibited Manoeuvres
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.
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Pilot’s Operating Handbook
Model J120-C
3.7
POWER PLANT LIMITATIONS
RPM
Maximum
Temperatures
POWER
Cyl Head
Absolute
Limits
Maximum
Take-Off
(85 BHP)
Maximum
Cont
(85 BHP)
Continuous
Limits
Limits For
Ground
Running
Oil
Fuel Pressure
Limits
Oil Pressure
Min
Max
Min
Max
Limits
3300
200 °C
(392°F)
(Note #1)
118°C
(244°F)
5 kPa
(0.75psi)
20 kPa
(3psi)
220 kPa
(31 psi)
525 kPa
(76psi)
3300
180°C
(356°F)
100°C
(212°F)
5 kPa
(0.75psi)
20 kPa
(3psi)
220 kPa
(31 psi)
525 kPa
(76 psi)
N/A
180°C
(356°F)
(Note #2)
100°C
(212°F)
(Note #2)
5 kPa
(0.75psi)
20 kPa
(3psi)
80 kPa
(11 psi)
525 kPa
(76 psi)
N/A
Note #1 Time with CHT at between 180°C and 200°C is not to exceed 5 Minutes
Note #2 If temperature limits are reached, shut the engine down or cool it by pointing the
aircraft into wind.
Table 2.4.2
Other limits are as follows:
•
•
Minimum oil pressure at idle:
Maximum oil pressure at start:
3.8
80 kPa (11 psi)
525 kPa (76 psi)
Fuel Grade
Grade:
Avgas 100LL
Avgas 100/130
MOGAS with minimum Octane Rating of 95 RON1 may be used.
Do not use fuel additives such as Octane Boosters.
NOTE
As there are significant variations possible even between automotive fuels with the same values
of RON, MON or AKI, Jabiru Aircraft strongly recommend using AVGAS. Automotive fuels
should only be used where AVGAS is not available, and if used, must have the highest antidetonation rating practically available.
CAUTION
In the J120-C Jabiru Aircraft allow the use of Ethanol additive to fuel up to a ratio of 10%.
However, owners must be aware of the additional operational risks and maintenance
requirements for using Ethanol additives. Section Error! Reference source not found. contains
additional information.
3.8.1
Lubricating Oil
Oil Capacity 2.2 Litres.
Refer to Section 8 for additional details.
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Model J120-C
3.9
POWER PLANT INSTRUMENT MARKINGS
Instrument
Red Line
Minimum Limit
Tachometer
-
Cylinder Head
Temperature
Oil Pressure
Oil Temperature
Fuel Pressure
-
Green Arc
Red Arc/Line
Yellow Arc
Precautionary
Range
Normal
Operating
Maximum Limit
-
3300 RPM
-
Up to 180°C
200°C
180°C - 200°C
(356°F)
(392°F)
(356° - 392°F)
80 kPa
220 - 525 kPa
525 kPa
80 - 220 kPa
(11 psi)
(31 – 76 psi)
(76 psi)
(11- 31psi)
15°C
80 - 100°C
118°C
100°C - 118°C
(59°F)
(176° - 212°F)
(244°F)
(212 °- 244°F)
5 kPa
5 – 20 kPa
20 kPa
(0.75psi)
(0.75 – 3 psi)
3 psi
-
10.5 – 15 Volts
-
Voltage
-
Table 2.5
3.10
REQUIRED EFIS DISPLAYS
Where aircraft are equipped with an EFIS display, they are programmed to display limitations and
alarms etc as a part of their installation into the aircraft. These limitations must be displayed for
the aircraft to comply with it’s certification basis. If adjustments are required to the displays the
work must be carried out before further flight by an authorised person with reference to the user
manuals for the instruments, and the following lists give the minimum information which must be
displayed.
3.10.1
Required EFIS limitation displays:
•
Never exceed speed, VNE (Red line speed, top of yellow arc)
•
Maximum structural cruising speed, VC (Top of green arc, bottom of yellow arc)
•
Maximum Flap Extension speed, VFE (Top of white arc)
•
Stall speed with full flap, VS0 (Bottom of white arc)
•
Stall speed clean, VS1 (bottom of green arc)
3.11
•
•
3.12
OTHER LIMITATIONS
Smoking is prohibited.
In-Cabin noise levels exceed 95 db. Hearing protection must be worn.
PLACARDS
The following placards are required, and are to be located in the proximity indicated. Each
placard is to contain wording conforming with the illustrations. The shape and layout of
production items may vary between individual aircraft. Consult the manufacturer for individual
aircraft placard variations.
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Model J120-C
3.12.1
Cockpit Placards General
Warning Placard
P/No. 5A092A0D
Fitted on the rear Face of the Forward Wing Spar Carry-through Beam
in the Cabin Ceiling.
LSA Placard
P/No. 5A060A0D
Fitted on the rear Face of the Forward Wing Spar Carry-through Beam
in the Cabin Ceiling.
No Intentional
Spins.
P/No. 5A072A0D
Fit to Instrument Panel
Owners Manual
P/No 5A075A0D
Fitted to Inside of RH Door above the Door Pocket.
No Smoking
P/No. 5A035A0D
Fit to instrument panel.
Door Open LHS
P/No 5027094
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
Fuel Contents
P/No. 5090064
Fitted to centre of front face of fuel tank between seats
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Model J120-C
Compass Card
P/No. 5123024
Fit in compass card holder attached to compass.
Baggage
P/No. 5A037A0D
Fit to right side fuselage wall immediately below window.
Baggage
P/No. 5111154
Fit to inside of fuselage on right side just below rear quarter window.
Locate vertical line in line with rear of fuel tank.
Loading
Limitations
P/No 5118024
Fitted on inside of fuselage of RHS of cabin below rear quarter
window.
Table 2.15.1
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Model J120-C
Cockpit Controls
Trim Position
P/No. 5024094
(1 OFF)
Fit to centre console beside of elevator fwd stop, above trim lever.
Fuel Tap Position
P/No 502319N
Fitted on the centre console beside the Fuel Selector Valve
Carby Heat
P/No 5A030A0D
Fitted to lower central section of instrument panel.
Table 2.15.2
External Fuselage
Static Port
STATIC VENT KEEP CLEAR
P/No 5043094
Attach to LHS of Vertical Fin in line with Static Tube
Fuel Grade- Wing
Tanks
P/No 5091064
Attach to fuselage adjacent to Fuel Filler Cap.
Nose Wheel
Inflation.
P/No. 5A017A0D
Attach to left side of nose wheel spat.
Main Wheel
Inflation.
P/No. 5A018A0D
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Model J120-C
Attach to outsides of main wheel spats
Engine Oil
P/No. 5A008A0D
Attach to inner face of door in top engine cowl.
Dipstick Inside
P/No. 5A007A0D
Fit to outside of oil door in upper engine cowl.
Door Lean.
P/No. 5A013A0D
Fit to top of doors.
Wing Bolt
Tightening
DANGER DO NOT TIGHTEN
P/No 5039094
Qty 8 Required
Attach to the fuselage and wings beside each wing, and lift strut
attachment fitting.
Earth on Post
P/No. 5A066A0D
Attach to upper wing skin beside fuel filler earth post.
No Step
P/No. 5A006A0D
Qty 2 required.
Fit to top of main wheel spats
Earth on Exhaust
P/No. 5029094
Attach to the lower fuselage on the pilot’s side immediately above the
exhaust outlet pipe.
Table 2.15.3
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Model J120-C
4
SECTION 4 – WEIGHT & BALANCE INFORMATION
4.1
CENTRE OF GRAVITY LIMITS
1601-mm (63.03”, 20%MAC) aft of datum up to & including
420 kg (926lb)
Forward Limit:
1661-mm (63.39”, 26.1%MAC) aft of datum at 500kg
(1190lb)
Linear variation between points.
Aft Limit
1695-mm (66.73”, 29.5%) aft of datum at all weights
Datum
1403mm fwd of RHS Wing Leading Edge
Levelling Means
Longitudinal
Spirit Level placed on the trim decal on the centre console.
Lateral
Spirit Level placed on the flap cross shaft.
Arms
Arm for Front Seat Station
1688-mm aft of datum
Arm for Baggage On Shelf
2280-mm aft of datum
Fuel Station
2280-mm aft of datum
Table 6.4 – Centre of Gravity Limits
Figure 6.3.1 – Baggage Zones
Baggage is restrained using the straps fitted in the baggage areas.
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Model J120-C
INSERT PAGES 6.2 & 6.3 FROM WEIGHING SPREADSHEET HERE
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INSERT WEIGHT & BALANCE RECORD FROM WEIGHING SPREADSHEET IN PLACE OF
THIS PAGE.
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Model J120-C
4.2
Trim Sheets
A metric trim sheet has been provided. An example loading has been worked through for
reference.
4.2.1
Trim Sheet Index Units
To use the trim sheets the aircraft’s weight and balance information must be converted to “Trim
Sheet Index Units” using the formula below:
Trim Sheet Index Units = Aircraft Weight x (Arm – 1403)
1000
“Aircraft Weight” and “Arm” are written onto the aircraft’s Load Data Sheet.
For example, an aircraft with “Aircraft Weight” of 260kg and “Arm” of 1590mm has a Trim Sheet
Index Unit of 48.62 This is used for the starting point of using the Trim Sheets.
Calculate Aircraft Weights
1-1
Use the Aircraft Empty Weight obtained from the latest aircraft weighing records to
enter the vertical “Aircraft Empty Weight Scale” on right hand side of the chart.
1-2
Move horizontally to the left into the next scale which is the “Crew Weight” Scale.
1-3
Move vertically downward one line on this scale for each 10-kg of weight that is
placed on the front seats, and mark a point.
1-4
Move horizontally to the left from the point made in Step 1-3 to enter the next scale
which is the “Baggage Weight” Scale.
1-5
Move vertically downward one line on this scale for each 5-kg of weight that is placed
in Baggage Zone and mark a point.
1-6
Move horizontally to the left from the point made in Step 1-7 to enter the next scale
which is the “Fuel Quantity” Scale and mark a point, This point is the “Zero Fuel
Weight Reference Point”
1-7
Move Horizontally to the left of the “Zero Fuel Reference Point” and Mark a “Zero
Fuel Weight Line” across the “Aircraft Trim Condition” Graph.
1-8
From the “Zero Fuel Point” on the “Fuel Quantity Scale” (marked in Step 1-8), move
vertically downward one line for each 10-litres of fuel being carried at the take-off
condition. Mark this “Take-Off Fuel Point” on the scale.
1-9
Move horizontally to the left, and mark a “Take-Off Fuel Weight Line” across the
“Aircraft Trim Condition” graph.
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Model J120-C
Calculating the Operating CG Locations
2-1.
Take the calculated Empty Weight Trim Index and mark it’s position on the Aircraft
Index Units Ladder at the top of the sheet.
2-2
Draw a vertical line down from the point marked above to intersect with a sloping line
in the “Crew Index Units” scale and mark this point.
2-3
Calculate the weight of the crew and round this value to the nearest 10-kg.
2-4
Move horizontally to the right from the point marked in Step 2-2 one line for each 10kg of load calculated. (i.e. 60-kg = 6 lines) and mark a point at this location.
2-5
Draw a vertical line down from the point marked above to intersect with a sloping line
in the Baggage Area scale and mark this point.
2-6
Calculate the weight that will be placed Baggage Area and round this value to the
nearest 5-kg.
2-7
Move horizontally to the right from the point marked in Step 2-5 one line for each 5kg of load calculated. (i.e. 20-kg = 4 lines) and mark a point at this location.
2-8
Drop a vertical line down from the point marked in Step 2-10 to intersect a sloping
line in “Fuel Chart”, and mark a point at this location.
2-9
Continue the Vertical Line began in Step 2-11 down to intersect with the “Zero Fuel
Weight Line” drawn in Step 1-7. mark this point as the “ZERO FUEL Condition”
2-10
Move horizontally to the right from the point marked in Step 2-11 in the “Take-Off
Fuel Box”, one line for each 10 liters of take-off fuel, and mark this point.
2-11
Move vertically downward from the take-off fuel point marked in Step 2-13 to
intersect with the “Take-Off Fuel Weight Line” marked in Step 1-9. Mark this point
the “Take-Off Condition”
4.2.2
Allowable Loading Conditions
An allowable loading condition exists when both the “Zero Fuel Condition”, and the “Take-Off
Condition” fall with the area bounded by the Line in the Aircraft Trim Conditions Box.
For reference, the example below shows two 80kg people, 5kg in Baggage Zone and 60L of fuel.
The aircraft’s starting Index Unit is 48.6 at 260kg.
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Model J120-C
EXAMPLE
45
55
65
Aircraft Index Units
75
85
95
105
115
125
135
145
STEP 1: Start at the empty aircraft's index
STEP 3A
Fuel Index Units - Come right 1 line per 10L fuel added.
-250
-250
-270
-270
-290
-290
-310
-330
-350
-310
Step 6: Check that the aircraft's CG position is
within the envelope with BOTH the fuel at the
start of the flight and at zero fuel.
-330
STEP 5: Starting from the aircraft empty
weight, draw a line as shown, c oming down 1
line per 10kg crew weight, 1 line per 5 kg
baggage and 1 line per 10 Litres of fuel.
-370
-390
-350
-370
-390
-410
-410
-430
-430
-450
-450
-470
-470
-490
-490
-510
-510
-530
-530
Figure 6-3a – Loading Trim Sheet Example
JP-FM-10
Aircraft
Empty Weight
Start at the
aircraft's empty
weight
every 10L of Fuel.
Crew Ladder
Go down 1 line
per 10kg crew
weight.
STEP 4
Baggage
Ladder
Go down 1
line per 5kg
STEP 3
Fuel Ladder
Go down 1
line per 10L
fuel.
Crew Index Units - Come right 1 line per 10kg Crew Weight.
STEP 3: Draw a line down from the Aircraft Index to
the Crew Index ladder. Move 1 line right for every
10k g of crew, every 5kg in Baggage Zone.
STEP 4: Draw a line straight down from Baggage
Baggage
UnitsIndex
- Come
right
1 line
per
Zone
Index Index
to the Fuel
. Move
1 line
right
for5kg added
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Jabiru Aircraft
Pilot’s Operating Handbook
Model J120-C
ORIGINAL
45
55
65
75
85
95
105
115
125
135
145
Aircraft Index Units
Fuel Index Units - Come right 1 line per 10L fuel added.
Crew Ladder
Go down 1 line
per 10kg crew
weight.
z
Baggage
Ladder
Go down 1 line
per 5kg
Fuel Ladder
Go down 1
line per 10L
fuel.
Baggage Index Units - Come right 1 line per 5kg added
Aircraft
Empty Weight
Start at the
aircraft's empty
weight
Crew Index Units - Come right 1 line per 10kg Crew Weight.
-250
-250
-270
-270
-290
-290
-310
-310
-330
-330
-350
-350
-370
-370
-390
-390
-410
-410
-430
-430
-450
-450
-470
-470
-490
-490
-510
-510
-530
-530
Figure 6.3b – Blank Trim Sheet
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Model J120-C
5
SECTION 5 – PERFORMANCE
5.1 TAKE OFF AND LANDING DISTANCES
Take-Off Distance
400 m
Landing Distance
300 m
Note:
All distances quoted are for an aircraft at gross weight, operating from a paved runway surface at
sea level in an ICAO standard atmosphere.
5.2 RATE OF CLIMB
Rate of Climb at Sea Level3
500 fpm
Note:
All distances quoted are for an aircraft at gross weight, operating from a paved runway surface at
sea level in an ICAO standard atmosphere.
5.3 CRUISE SPEEDS / RPM / FUEL CONSUMPTION
•
•
3
Cruise speed values given are based on tests carried out at gross aircraft weight, at sea
level and around 28°C. Values are averaged. Actual values will vary slightly from one
aircraft to the next. Values used for flight planning should be based on previous experience
with the specific aircraft wherever possible.
Fuel consumption values given are averaged. Actual values will vary slightly from one
aircraft to the next. Values used for flight planning should be based on previous experience
with the specific aircraft wherever possible.
RPM
Fuel Consumption
(Litres/hr)
IAS
(Knots)
2600
11
100
2700
13.5
107
2800
15
105
2850
16
110
2900
17
115
3000
18
118
At Gross Weight, ICAO Standard Atmosphere
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5.4 Airspeed Indicator System Calibration
Conditions:
Power:
As required for level flight or maximum rated RPM as appropriate.
KCAS
KIAS
JP-FM-10
Flaps UP
Flaps Take-off
Flaps Landing
47
-
-
45
49
-
47
47
50
-
48
48
51
49
49
49
56
53
54
54
57
54
55
55
63
60
60
60
73
70
70
70
85
81
82
82
94
90
90
90
106
101
-
-
113
108
-
-
117
112
-
-
125
120
-
-
135
129
-
-
146
140
-
-
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Jabiru Aircraft
Pilot’s Operating Handbook
Model J120-C
6
SECTION 6 - EMERGENCY PROCEDURES
6.1
GENERAL
This Section describes the procedures to be adopted in the event of an emergency or abnormal
situation occurring in the J120-C aircraft.
The procedures are arranged in the sequence considered to be the most desirable in the majority
of cases. Steps should be performed in the order listed unless good reasons for deviation exist.
It should be remembered however, that all conceivable eventualities cannot be foreseen by the
manufacturer. Particular circumstances such as multiple or unanticipated emergencies, adverse
weather etc. may require modification to these procedures. A thorough knowledge of the aircraft
and its systems is essential to analyse the situation correctly and determine the best course of
action in any particular circumstance.
The following basic rules apply to all aircraft emergencies:
1.
2.
3.
6.2
Maintain Aircraft Control.
Analyse the situation and take appropriate action.
Land as soon as practicable.
AIRSPEEDS FOR EMERGENCY OPERATIONS
Maximum Glide ……………………………………………. 65 KIAS*
Landing Without Engine Power (Flaps Full) …………… 60 KIAS
* - A slightly higher speed may give better distance over the ground if gliding into wind; a slightly
slower speed if gliding downwind.
6.3
6.3.1
EMERGENCY PROCEDURES CHECK LISTS
Engine Failures
Engine Failure During Take-off Run
1.
2.
3.
4.
5.
6.
Throttle.................................................................. CLOSED
Brakes................................................................... APPLY
Ignition .................................................................. OFF
Wing Flaps ............................................................ UP
Master Switch........................................................ OFF
Fuel Shutoff Valve ................................................. OFF
Engine Failure Immediately After Take-off
1.
2.
3.
4.
5.
6.
Airspeed……………………………………………….. 65 KIAS.
Ignition…………………………………………………. OFF (As time permits)
Fuel Shutoff Valve……………………………………. OFF (As time permits)
Wing Flaps……………………………………………..FULL RECOMMENDED
Master Switch………………………………………….OFF
Braking………………………………………………… HEAVY AFTER TOUCHDOWN
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Jabiru Aircraft
Pilot’s Operating Handbook
Model J120-C
Engine Failure During Flight
1.
2.
3.
4.
5.
6.
7.
8.
9.
Airspeed………………………………………….65 KIAS*.
Carburettor Heat……………………………….. ON
Fuel Pump………………………………………. ON
Fuel Shutoff Valve……………………………… CONFIRM ON
Fuel Quantity…………………………………….CHECK
Oil…………………………………………………CHECK TEMP AND PRESSURE
Ignition……………………………………………CYCLE BOTH ON
Throttle…………………………………………...CHECK LINKAGE OPERATION
Airstart…………………………………………… ATTEMPT IF PROP STOPPED
* - A slightly higher speed may give better distance over the ground if gliding into wind; a slightly
slower speed if gliding downwind.
6.3.2
Airstart & Limitations
In the event that the engine is stopped during flight, it may be restarted by application of fuel &
ignition, provided that the propeller is still windmilling. The propeller may stop windmilling below
50 KIAS
The Jabiru 2200 engine is a high compression (7.8:1) engine & therefore airstarts when the
propeller has stopped rotating, without the use of the starter, are unlikely before reaching VNE.
Therefore, the following procedure addresses only airstarts by use of the starter motor.
IMPORTANT – NO NOT depress starter button while propeller is rotating.
Notes:
1.
2.
3.
Ignition……………………………………………OFF
Cabin…………………………………………….. CLEAR
Airspeed………………………………………….REDUCE UNTIL PROPELLER
STOPS TURNING.
4.
5.
6.
7.
8.
9.
10.
11.
Establish Glide…………………………………..65 KIAS
Fuel……………………………………………….ON
Fuel Pump………………………………………. ON
Master…………………………………………… ON
Ignition Switches……………………………….. ON
Starter Button…………………………………… Depress
Throttle…………………………………………...Open
Repeat as necessary, ensuring propeller has stopped before each restart attempt.
(a)
If engine does not restart commence forced landing procedure.
(b) If clear symptoms of a mechanical failure exist, or if the engine has seized
due to the loss of oil pressure, do not attempt a restart.
JP-FM-10
(c)
If engine operates with only L or R ignition selected, leave the ignition switch in
this position whilst a suitable landing area is selected.
(d)
The engine cools quickly with the propeller stopped.
achieve a start.
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Jabiru Aircraft
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Model J120-C
6.3.3
Forced Landings
Emergency Landing Without Engine Power
1.
2.
3.
4.
5.
6.
7.
8.
Airspeed…………………………………….... 65 KIAS
Ignition…………………………………………OFF
Fuel Shutoff Valve…………………………… OFF
Fuel Pump……………………………………. OFF
Throttle………………………………………... CLOSED
Wing Flaps…………………………………… FULL PRIOR TO TOUCH DOWN
Master Switch………………………………... OFF
Braking………………………………………... HEAVY AFTER TOUCH DOWN
Precautionary Landing With Engine Power
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
Airspeed .....................................................70 KIAS
Fuel Pump..................................................ON
Wing Flaps .................................................TAKE-OFF
Selected field..............................................OVERFLY & INSPECT
Wing Flaps .................................................FULL ON FINAL APPROACH
Airspeed .....................................................60 KIAS
Braking .......................................................HEAVY AFTER TOUCH DOWN
Ignition........................................................OFF
Fuel Shutoff Valve ......................................OFF
Master Switch.............................................OFF
Ditching
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
6.3.4
Airspeed .....................................................65 KIAS
Power (if available) .....................................ESTABLISH 50 ft/min @ 55 KIAS
Approach
High Winds, Heavy Seas ............................INTO WIND
Light Winds, Heavy Swells………………….PARALLEL TO SWELLS
Wing Flaps .................................................FULL PRIOR TO TOUCH DOWN
Doors..........................................................OPEN
Face ...........................................................CUSHION AT TOUCH DOWN
Touch Down ...............................................SLOWEST PRACTICAL SPEED
Evacuate ....................................................IF REQUIRED BREAK WINDOWS
Life Jackets / Life Rafts...............................INFLATE
EPIRB (If Carried).......................................ACTIVATE
Fires
On Ground
1.
2.
3.
4.
5.
6.
JP-FM-10
Ignition........................................................OFF
Fuel Shutoff valve.......................................OFF
Fuel Pump..................................................OFF
Master Switch ............................................OFF
Abandon aircraft
Fire.............................................................EXTINGUISH
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Jabiru Aircraft
Pilot’s Operating Handbook
Model J120-C
Engine Fire In Flight
1.
2.
3.
4.
5.
6.
7.
8.
9.
Throttle....................................................... CLOSE
Fuel Valve .................................................. OFF
Fuel Pump.................................................. OFF
Ignition ....................................................... OFF
Master Switch............................................. OFF
Cabin Heat Vent......................................... CLOSE
Cabin Air Vent ............................................ OPEN BOTH
Airspeed .................................................... INCREASE UP TO VNE if required to
extinguish fire.
Forced Landing .......................................... EXECUTE. Refer 3.3.3
Electrical Fire In Flight
1.
2.
3.
4.
Master Switch............................................. OFF
Ignitions...................................................... ON
Electrical Switches ..................................... OFF
Extinguisher ............................................... ACTIVATE
If fire goes out:
5.
6.
Smoke........................................................ VENTILATE CABIN (DOORS MAY
BE OPENED SLIGHTLY)
Precautionary Landing................................ AS SOON AS PRACTICAL
If fire does not go out:
4.
Land........................................................... EXECUTE IMMEDIATELY
WARNING
With the Master Switch turned off the wing flaps will not deploy.
Cabin Fire
1.
2.
3.
4.
5.
6.
Master Switch............................................. OFF
Cabin Heat Vent......................................... CLOSE
Cabin Air Vent ............................................ OPEN BOTH
Extinguisher (if fitted).................................. ACTIVATE
Land........................................................... AS SOON AS PRACTICAL
Smoke/Fume Evacuation ........................... VENTILATE CABIN. DOORS MAY
BE OPENED SLIGHTLY.
Once fire is extinguished:
1. Power......................................................... REDUCE
2. Airspeed..................................................... APPROX 80 KIAS
3. Cockpit Door(s) .......................................... CLOSE
4. Power......................................................... ADJUST to maintain approx 80 KIAS
5. Land........................................................... AS SOON AS PRACTICAL
NOTE
Doors should only be opened for emergency fume evacuation
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6.3.5
Carburettor Icing
If Carburettor icing is suspected:
1.
2.
Throttle .......................................................FULL
CARB HEAT...............................................FULL ON
NOTE
Carburettor heat may be used at any power setting, but will result in a slight power loss. When
icing is eliminated, return CARB HEAT to OFF. Carburettor heat should not be used for takeoffs.
Maintain carburettor heat in ON position for a minimum of 1 minute to allow all ice to melt.
Carburettor heat may be used on the ground except during take-off.
CAUTION
Do not use partial carburettor heat as this may exacerbate ice accretion.
6.3.6
Landing With a Flat Main Tyre
1.
2.
3.
4.
5.
6.
7.
6.3.7
Landing Area ..............................................SUITABLE
Approach....................................................NORMAL
Wing Flaps .................................................FULL DOWN
Touchdown.................................................GOOD TYRE(S) FIRST, hold aircraft
off flat tyre as long as possible with
aileron and/or elevator control
Ignition........................................................OFF
Fuel Shutoff Valve ......................................OFF
Master Switch.............................................OFF
Inadvertent Icing Encounter
Flight into known icing conditions is prohibited. If icing is inadvertently encountered,
change level or turn back to obtain an outside air temperature less conducive to icing.
6.3.8
Spins
Intentional spins are prohibited in this aircraft.
following recovery procedure should be used:
1.
2.
3.
4.
5.
6.
Should an inadvertent spin occur, the
Retard the throttle to idle
Centralise ailerons
Apply and hold full rudder opposite to the direction of rotation
Move stick progressively forward far enough to break stall
Hold these control inputs until rotation stops
As rotation stops, centralise rudder and make a positive, smooth recovery from
the resulting dive
WARNING
If the spin is encountered with flaps extended, DO NOT retract flaps until rotation ceases.
Premature flap retraction will delay recovery.
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Model J120-C
7
SECTION 7 – NORMAL PROCEDURES
7.1
GENERAL
Section 4 of this handbook describes the procedures to be adopted for normal operations of the
J120-C aircraft.
The procedures are arranged in the sequence considered to be the most desirable and therefore
steps should be performed in the order listed unless good reasons for a deviation exist.
7.2
SPEEDS FOR NORMAL OPERATION
Unless otherwise noted, the following speeds are based on a maximum weight of 500 kg
(1102lb) and may be used for any lesser weight.
Take-Off:
T.O.S.S. (Speed @ 50 ft) .............................65 KIAS
Normal Climb Out.........................................70 KIAS (Take Off Flap)
Climb, Flaps Up:
Initial (scheduled climb) ................................70 KIAS
Enroute ........................................................70-80 KIAS
Landing Approach:
VREF (Speed @ 50 ft) ....................................65 KIAS
Baulked Landing...........................................65 KIAS Initially
Maximum Recommended in Turbulence:
7.2.1
All Weights ...................................................108 KIAS
Best Angle of Climb Speed
7.2.2
VX – Best angle of climb speed.....................65 KIAS
Best Rate of Climb Speed
VY – Best Rate of climb speed ..........................68 KIAS
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Model J120-C
7.3
PREFLIGHT INSPECTION
Before flight, a careful visual inspection is to be carried out to ensure that the aircraft and its
systems are serviceable. The following Figure is to be used in conjunction with the preflight
inspection checklist:
Figure 4-1. Pre-flight Inspection
1. Cockpit
Ignition Switches ..................................... OFF
Control lock (if fitted)................................ REMOVE
Fuel ......................................................... CHECK CONTENTS
Fuel valve................................................ ON
Master switch .......................................... ON
Alternator Warning Light .......................... CONFIRM ON Before Start
Master Switch.......................................... OFF
Aileron and elevator cables & fasteners... CHECK
Rudder and nose wheel steerage linkage CHECK
Rudder centring springs........................... CHECK
Controls (all)............................................ CHECK full travel, free movement.
Harnesses & Seats.................................. CHECK CONDITION
Windshield............................................... CLEANLINESS
Cockpit area ............................................ GENERAL CONDITION
Loose objects .......................................... SECURE
Cockpit Doors/Latches ............................ CONDITION & OPERATION
Flight Manual........................................... AVAILABLE
2. Left Undercarriage
Mount bolts.............................................. CHECK SECURE*
Tyre......................................................... CHECK CONDITION / INFLATION
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* - Lock the hand brake on, then pull the aircraft forwards. Some flexing of the undercarriage legs
is normal, but there should be no movement of the top of the leg relative to the fuselage.
3. Fuel
Quantity in both tanks...............................Check
Fuel caps .................................................Secure
Water Check ............................................Both tanks and header tank
4. Static Source
Static Source............................................CHECK FOR BLOCKAGE
5. Empennage
Tail tie-down.............................................DISCONNECT
Control surfaces .......................................CHECK Security & Full & Free Movement
Rudder, Elevator & Trim Cables ...............CHECK Security & Full & Free Movement
6. Right Wing – Trailing Edge
Aileron......................................................CHECK Security & Full & Free Movement
Flap..........................................................CHECK Security
Control rods & cables ...............................CHECK Security. Check rod ends for
freedom of rotation & excess movement.
7. Right Wing
Wing Tie-Down.........................................DISCONNECT
Wing Strut Mount Bolts.............................CHECK Security**
Wing Root Mount Bolts.............................CHECK Security***
Pitot Tube.................................................REMOVE COVER, CHECK for blockage.
** - Wing strut bolts must not be tightened. Nut should just bear on washer.
*** - Holding the wingtip, push the tip up & down, forwards & backwards. If a wing / strut
attachment is degrading, slop will be felt.
8. Nose
Propeller & Spinner ..................................CHECK for nicks & security
Cowl.........................................................CHECK Security, rubbing on engine.
Engine Oil ................................................CHECK using oil filler door.
Nose Wheel .............................................CHECK condition & pressure.
9. Left Wing
Wing Tie-Down.........................................DISCONNECT
Wing Strut Mount Bolts.............................CHECK Security**
Wing Root Mount Bolts.............................CHECK Security***
10. Left Wing – Trailing Edge
Aileron......................................................CHECK Security & Full & Free Movement
Flap..........................................................CHECK Security
Control rods & cables ...............................CHECK Security. Check rod ends for
freedom of rotation & excess movement.
11. “Pulling Through” The Engine
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Model J120-C
Before the first flight of the day the engine must be “pulled through” by hand. This is the process
of turning the engine over by turning the propeller by hand. The compression of each cylinder in
turn will be felt a resistance as the propeller is turned. The engine should be rotated for a count
of at least 8 compressions.
Master Switch............................................OFF
Ignitions.....................................................OFF
Throttle......................................................Closed
Propeller....................................................TURN by hand & observe engine for odd
noises or heavy movements. Check for
regular compression.
CAUTION:
Prior to pulling through the propeller by hand, the engine must be cold, both ignition circuits & the
Master Switch must be switched OFF, the brakes applied & throttle closed.
WARNING
A hot engine may fire with the ignition/s switched OFF.
DO NOT pull through a hot engine.
CAUTION
Several causes of irregular compression – such as poorly sealing valves – can lead to extensive
engine damage if not addressed. The Jabiru 2200 Engine Instruction & Maintenance Manual
provides additional details.
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7.4
7.4.1
NORMAL PROCEDURES CHECK LISTS
Before Starting Engine
Pre flight Inspection..................................COMPLETED
Passenger Briefing...................................COMPLETED
Harnesses................................................SECURE
Brakes......................................................ON/PARK
Avionics ...................................................OFF
Circuit Breakers........................................IN
Fuel Level Warning Light (if fitted) ............CHECK OPERATION using test switch
7.4.2
Starting Engine - Cold
Master Switch ..........................................ON
Fuel Shutoff Valve....................................ON
Carburettor Heat ......................................OFF
Choke ......................................................ON*
Throttle.....................................................CLOSED
Fuel Pump................................................ON
Ignition switches.......................................ON
Starter ......................................................ENGAGE when engine fires RELEASE**
Oil Pressure .............................................CHECK (pressure to be indicated within 10 secs)
Choke .....................................................Closed
Throttle ....................................................900 – 1000 RPM
Alternator Warning Light...........................CHECK OFF
Avionics ...................................................ON
* - If the engine is hot, proceed as for cold engine, but do not use choke.
** - If the engine is turning at less than 300 RPM it will not start.
7.4.3
Before Take-Off
Park Brake ...............................................ON
Ground Check & Run Up
Warm Up..................................................1000-1200 RPM avoid prolonged idle at low RPM
Ignition Check ..........................................2000 RPM Both-L-Both-R-Both. Max drop 100RPM
Carburettor heat .......................................2000 RPM – ON – slight drop in RPM
Carburettor heat ......................................2000 RPM – OFF – RPM restored
Power Check............................................2850 RPM +/- 150 RPM
Idle Check ................................................700 – 900 RPM
Trim..........................................................SET – Neutral
Pre Take-Off
Master Switch ..........................................ON
Ignition switches.......................................BOTH ON
Fuel Shutoff Valve....................................ON
Fuel Quantity............................................CHECK sufficient for task
Fuel Pump................................................ON
Flaps ........................................................TAKE OFF (first stage)
Instruments ..............................................SET AND CHECK ALL
Switches ..................................................SELECTED as required
Circuit Breakers........................................CHECK
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Model J120-C
Controls................................................... FULL & FREE TRAVEL, CORRECT SENSE
Hatches................................................... CLOSED & LOCKED
Harnesses ............................................... SECURE all seat belts correctly fastened and adjusted
Oil temperature........................................ ABOVE 500C
7.4.4
Take-Off
Carburettor heat ...................................... OFF
Throttle.................................................... FULL OPEN
Elevator Control....................................... NEUTRAL
Directional Control ................................... NOSEWHEEL STEERING & RUDDER
Rotate ..................................................... 30 – 40 KIAS raise nosewheel clear of ground
Take Off Safety Speed ............................ 66 KIAS
Accelerate to Climb Speed ...................... 70 KIAS
Flaps ....................................................... UP… Accelerate to 70 KIAS
Fuel Pump............................................... OFF at top of climb.
Power...................................................... SET as required.
7.4.5
Initial Climb
Throttle.................................................... FULL OPEN
Airspeed.................................................. 70 KIAS
7.4.6
Cruise
75% Power.............................................. 2800 RPM (14 L/hr)
7.4.7
Descent
Power...................................................... As required
Carburettor heat ...................................... As required
7.4.8
Before Landing (and flight below 1000ft AGL)
Brakes..................................................... OFF
Harnesses ............................................... SECURE
Fuel Pump............................................... ON
7.4.9
Landing
Airspeed @ 50ft....................................... 63 KIAS
Wing Flaps .............................................. FULL
Directional Control ................................... RUDDER & NOSEWHEEL STEERING
Power ..................................................... AS REQUIRED
Touchdown ............................................. Main wheels first
Braking.................................................... AS REQUIRED
NOTE
If the aircraft is contaminated by build up of insects or other debris, increase approach speed @
50ft to 68 KIAS
7.4.10
Baulked Landing
Power...................................................... FULL THROTTLE
Carburettor heat ..................................... COLD
Wing Flaps .............................................. RETRACT SLOWLY
Airspeed.................................................. ESTABLISH NORMAL CLIMB SPEED
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7.4.11
After Landing/Securing
Wing Flaps ...............................................UP
Fuel Pump................................................OFF
Parking Brake ..........................................ON/AS REQUIRED
Avionics ...................................................OFF
Ignition .....................................................OFF
Master Switch ..........................................OFF
Controls ...................................................SECURE
7.4.12
Engine Management – Ground Running
The 2200B engine fitted to the J120-C is cooled by air flowing over the engine and oil cooler.
During ground running care must be taken to ensure that there is adequate airflow and that safe
engine temperatures are maintained. The guidelines presented below will assist in controlling
temperatures.
Minimise ground running times – especially in hot weather4.
Carry out as many checks as possible before starting the engine.
Always carry out engine run-up tests with the aircraft pointing into wind.
In hot weather, after performing run-up checks, leave the aircraft pointing into wind and idling
at 1200rpm for 30 seconds to aid cooling.
If the aircraft is required to wait – such as for runway clearance – temperatures must be
monitored, and if they approach ground running limits (listed in Section 2 of this flight manual
& displayed as yellow markings on engine gauges) the aircraft must be turned into wind or
shut down to prevent any further temperature increase.
Wind must be coming from within approximately 45° of the aircraft heading to be effective in
aiding engine cooling.
If there is no wind or low wind the engine must be shut down if ground-running temperature
limits are reached.
•
•
•
•
•
•
•
8
4
30°C and above
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SECTION 8 – GROUND HANDLING & SERVICING
8.1 FUEL
•
•
•
•
Avgas 100LL
Avgas 100/130
MOGAS with minimum Octane Rating of 95 RON1 may be used.
Do not use fuel additives such as Octane Boosters.
NOTE
As there are significant variations possible even between automotive fuels with the same values
of RON, Jabiru Aircraft strongly recommend using AVGAS. Automotive fuels should only be
used where AVGAS is not available, and if used, must have the highest anti-detonation rating
practically available.
CAUTION
Fuel additives containing alcohol (i.e. Ethanol etc) will damage the sealant used in the fuel tanks.
DO NOT use fuel with any level of added alcohol.
8.1.1
Fuel Ethanol Content
Jabiru Aircraft allow fuels with an Ethanol content of up to 10% to be used in the J120-C. While
Ethanol boosts the fuel’s octane rating and is becoming increasingly common in automotive fuels
there are important issues caused by its use. The following points are given as a basic
introduction to using Ethanol. Note that while this information was current at the time of writing.
•
•
Use of a fuel with an Ethanol content higher than 10% IS NOT PERMITTED in the J120-C.
•
Ethanol mixed with water is somewhat corrosive and may attack fittings etc of the fuel
system.
•
In long-term storage, Ethanol may oxidise with exposure to air. This process produces a
mild acid solution (vinegar) which can attack fuel system fittings.
•
Long term exposure to Ethanol damages some types of plastics. The J120-C details
replacement times for fuel lines which are designed with Ethanol fuel blends in mind,
however increased monitoring of fuel lines is recommended in an aircraft using Ethanol
blends.
•
Some fuel testers (including the type supplied by Jabiru Aircraft at the time of writing) have
a scale on their side which allows the Ethanol content of a fuel to be checked & assessed.
Ethanol is hygroscopic (i.e. it will absorb water). This can be water vapour from the air,
condensation inside tanks or free water. While very small amounts of water can be
absorbed without significantly affecting the fuel’s combustion, at higher levels the mixture
will not be combustible. In addition, because this incombustible fuel is formed from a
mixture of the Ethanol in the fuel and the water it can have a large volume – so a small
amount of water will result in a much larger amount of incombustible Ethanol/water mix.
This may give false readings in the fuel tank sumps or exceed the volume of the sump
altogether.
Several CASA documents discuss Ethanol, and Jabiru Aircraft strongly recommend that owners
considering using an Ethanol fuel blend read and understand this information before using a fuel
of this type. The following CASA document is current at the time of writing:
•
Airworthiness Bulletin AWB 2828-003003
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8.2 OIL
8.2.1
Engine Oil Specification:
Jabiru Aircraft approves lubricating oils of any brand name conforming to specifications MIL-L6082 for straight mineral oil and MIL-L-22851 for ashless dispersant oil.
Straight mineral oil must be used during the first 50 hours of operation for new and overhauled
engines, or until the oil consumption has stabilised. After the first 50 hours it is recommended
that ashless dispersant oil be used.
8.2.2
Engine Oil Viscosity Grade:
The following chart is intended to assist in choosing the correct grade of oil and must be
considered as a guide only. Multiviscosity grades can also be used as indicated
Average
Ambient Temperature
Mineral
Grades
Ashless Dispersant
Grades
Above 35° C (95°F)
SAE 60
SAE 60
SAE 50
SAE 50
SAE 40
SAE 40
15° C to 35°C
(59° to 95°F)
-17°C to 25°C
(1° to 77°F)
Equivalence of SAE and commonly used Commercial Grade designations:
SAE:
20
30
40
50
60
Commercial:
55
35
80
100
120
8.3 BRAKES
The brakes of the J120-C use automotive brake fluid. Refer to the J120 Technical manual for
details of appropriate brake fluid specifications.
WARNING:
The JABIRU uses automotive brake fluid (DOT 3 or DOT 4). DO NOT use Aircraft hydraulic fluid
(mineral based) or damage to the brake system will result.
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Model J120-C
9
9.1
SECTION 9 – SUPPLEMENTS
INTRODUCTION
This section consists of a series of supplements, each being self contained and providing details
and procedures associated with the fitment of optional and special purpose equipment.
Each supplement contains a brief description, and where applicable, operating limitations,
emergency and normal procedures, and the effect on aircraft performance. The data contained
in a supplement adds to, supersedes, or replaces similar data in the basic POH when operating
in accordance with the provisions of that supplement.
It is the owner’s responsibility to ensure that new Jabiru Aircraft Supplements received after
receipt of the POH are recorded on the Log of Supplements page.
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Model J120-C
9.2
SUPPLEMENT LOG – JABIRU AIRCRAFT SUPPLEMENTS
Applicable to aircraft serial number J120-C ______________
Install
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