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Jabiru j160, Product Manual

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Jabiru j160 Product Manual Download Page 66

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66 

 

FOR SIMULATION USE ONLY 

 

Landing Configuration Climb 

Associated conditions: Power:

 Full Throttle 

Airspeed: 

60 KIAS 

Flaps: 

Land 

Sea Level Gradient of Climb: 6.8% (1:14.6) 

 

CRUISE 

The JABIRU 2200 engine has an altitude compensating carburettor which 
ensures that the fuel flow is constant at all operating altitudes.  

This feature has been examined by flight testing, and verified for altitudes 
between sea level and 5000 ft. 

 

Figure 4-7 Cruise Power Settings

 

NOTE 

•

 

The JABIRU 2200 engine has an altitude compensating carburettor  
which provides for a fuel flow that is constant at all operating altitudes.  
 

•

 

This feature has been examined by flight testing, and verified for 
altitudes between sea level and 5000 ft.  
 

•

 

Fuel flow values have not been verified above 5,000 ft. therefore pilots 
will need to monitor fuel flows to ensure accuracy when operating 
above that altitude. 
 

Summary of Contents for j160

Page 1: ...FOR SIMULATION USE ONLY FOR OFFICIAL USE ONLY AIR PUBLICATION 2020 001 AFM PRODUCT MANUAL JABIRU J160 J70 Original Date of Issue 1st October 2020 Software Version v2 0 0 ...

Page 2: ... 160 J170 product by IRIS Flight Simulation Software for Microsoft Flight Simulator Under NO circumstances is any component of this product intended to replace or compliment any form of real world training materials The intended use is for entertainment purposes ONLY ALWAYS refer to approved publications from the aircraft manufacturer when flying aircraft OPERATING INSTRUCTIONS This manual provide...

Page 3: ... Warnings Cautions and Notes found throughout the manual WARNING Operating procedures techniques etc which may result in personal injury or loss of life if not carefully followed For the purposes of this product this would mean the end of the simulation session CAUTION Operating procedures techniques etc which may result in damage to equipment if not carefully followed For the purposes of this pro...

Page 4: ...Manual correctly it is essential to understand the division of the manual into its sections and the subsequent division of the sections Each section has a table of contents and best use will be obtained from the Manual by becoming familiar with the table of contents for each section The index enables easy reference to a particular topic or item by page number CHECKLISTS The Flight Manual contains ...

Page 5: ...itches toggle on or move upwards a single click of the LEFT mouse button and toggle OFF or move downwards with a subsequent single click of the LEFT mouse button 2 Any multiple position switches three or more use a single click and drag function All knobs function in the following manner 1 If the knob is capable of being pushed in or clicked a single click of the LEFT mouse button will perform thi...

Page 6: ...I A P 2 0 2 0 0 0 1 A F M J A B I R U J 1 6 0 J 1 7 0 P a g e 6 FOR SIMULATION USE ONLY LIST OF ASSOCIATED PUBLICATIONS IAP 2020 001 ACL1 Abbreviated Checklists IAP 2020 001 PA Product Acknowledgements ...

Page 7: ... 2 0 2 0 0 0 1 A F M J A B I R U J 1 6 0 J 1 7 0 P a g e 7 FOR SIMULATION USE ONLY TABLE OF CONTENTS Page No SECTION 1 DESCRIPTION AND OPERATION 8 SECTION 2 NORMAL OPERATIONS 46 SECTION 3 PERFORMANCE DATA 62 ...

Page 8: ...HAPTER 1 DESCRIPTION AND OPERATION GENERAL 11 THE AIRCRAFT 11 Introduction 11 Dimensions 12 Gross Weight 12 AIRFRAME 13 Wings 13 Fuselage 13 Empennage 13 FLIGHT CONTROLS 14 Trim System 14 Adjustable Rudder Pedals 14 INSTRUMENT PANEL 15 ENGINE 17 Throttle 17 Choke 17 Auto Mixture System 18 Carburettor Heat 18 Engine Instruments 18 Engine Oil System 18 ...

Page 9: ...stem 20 Cooling System 20 GROUND CONTROL 21 WING FLAP SYSTEM 21 UNDERCARRIAGE SYSTEM 21 SEATS 22 BAGGAGE SHELF 22 ENTRANCE DOORS 22 PROPELLER 22 FUEL SYSTEM 23 System 1 23 System 2 23 Both Systems 23 BRAKE SYSTEM 24 ELECTRICAL SYSTEM 25 COCKPIT VENTILATION 26 PITOT STATIC SYSTEM AND INSTRUMENTS 26 Airspeed Indicator 26 Altimeter 26 Vertical Speed Indicator 26 ...

Page 10: ... 0 P a g e 10 FOR SIMULATION USE ONLY STALL WARNING SYSTEM 27 AVIONICS 28 Electronic Flight Instrumentation System 28 ADI Page 29 HSI Page VOR Mode 32 HSI Page GPS Mode 34 HSI Page LOC Mode 35 TIMER Page 37 COM Radio 38 NAV Radio 39 Transponder Radio 41 ...

Page 11: ...ne through a header tank located below the baggage shelf The cockpit is designed to accommodate the pilot in command on the left side and all controls instruments selectors and switches are located so as to be within easy reach of the occupant of that seat Conventional 3 axis flight controls and variable wing flaps are provided Duplicated flight controls are provided on the right side of the cockp...

Page 12: ...wn in Figure 1 2 Gross Weight J160 The aircraft basic empty weight is approximately 661 pounds Maximum take off gross weight is 1190 pounds Gross Weight J170 The aircraft basic empty weight is approximately 705 pounds Maximum take off gross weight is 1323 pounds These weights shall not be used for computing aircraft performance or for any type of operation Refer to Section 3 Operating Limitations ...

Page 13: ...gs The main fuel tanks are incorporated in the inboard section of the wings between the spar and the rear of the wing The ailerons are controlled via push pull Teleflex cables The wing flaps are powered by an electric motor driving through a mechanical linkage Fuselage The fuselage is of GRP construction The fixed horizontal and vertical tail surfaces are bonded to the structure Empennage The empe...

Page 14: ...ontrol is controlled via levers mounted on either side of the cockpit centre console The system consists of a cable operated system which uses springs connected to a friction lock to control the elevator control force Selection of nose up trim pivots the trailing edge of the elevator upwards Adjustable Rudder Pedals J160 J170 aircraft have the option of fitting adjustable rudder pedals These pedal...

Page 15: ...er is located centrally on the lower section of the panel while the other engine instruments are placed in a vertical row slightly to the right of the centre of the panel Where electric fuel gauges are fitted they are located centrally below the radios The right side of the panel is left empty to allow owner s to fit their choice of GPS system or other instrumentation A push pull throttle knob is ...

Page 16: ... AVIONICS 9 OIL PRESSURE INDICATOR 21 STARTER BUTTON 10 OIL TEMPERATURE INDICATOR 22 MAGNETOS AND MASTER SWITCH 11 CYLINDER HEAD TEMPERATURE 23 TURN AND SLIP INDICATOR 12 BATTERY VOLTAGE 24 SYSTEM INDICATOR LIGHTS NOTE Whilst the Generation 1 panel is shown in Option A configuration aircraft include both Generation I and Generation II panels in Option A or B configurations In all aircraft the core...

Page 17: ...M Throttle Engine power is controlled by a throttle located on the left and right sides of the instrument panel It is readily identified by smooth black cylindrical knobs The throttle operates in the conventional sense in that when fully forward the throttle is full open and in the fully aft position the throttle is closed Choke The choke is a push pull control located in the centre of the lower s...

Page 18: ...operation is monitored by a tachometer oil pressure and oil temperature fuel pressure and cylinder head temperature gauges These instruments are located in the instrument panel in front of the pilot and are marked with green arcs to indicate the normal operating range yellow arcs to indicate precautionary ranges and red lines at the maximum minimum allowable limits These limits and gauge markings ...

Page 19: ... single spark plug in each cylinder Normal operation is conducted with both magnetos on due to the more complete burning of the fuel air mixture with dual ignition sources The individual magnetos are selected using the two ON OFF toggle switches located on the left hand side of the instrument panel Starting System The electrically driven starter motor is mounted at the rear of the engine When ener...

Page 20: ...der feeds directly to the muffler via an extractor pipe The extractors fit to the head using a metal metal gasket less connection which also allows a degree of freedom to the extractor position A muff is fitted to the muffler to supply hot air for the carburettor heat system A separate hot air muff is fitted to the tail pipe to provide air for the cabin heat The exhaust tailpipe exits out through ...

Page 21: ... manually by the pilot a position indicator is fitted on the pilot s side A pillar between the windscreen and the front of the door opening The selected position can be easily confirmed by visual observation of the flaps The flap system is electrically actuated The flaps are extended by mechanical force provided by the flap motor operating on a torque tube and push rod mechanism The flap structure...

Page 22: ... provide a barrier against forward movement of the baggage items which are narrower than the full width of the shelf should be located centrally behind a seat back ENTRANCE DOORS A forward opening cockpit door is fitted to each side of the aircraft The door latch is a simple locking pin operated by a handle on both the inside and out These doors also act as emergency exits Opening of the doors in ...

Page 23: ...corner of each tank The two delivery pipes from each side join together in the fuselage wall below the wing Then the single delivery line continues to the header tank under the passenger s side of the baggage shelf Breathers for the wing tanks run from the outboard end of the tank and are connected with lines that run between the tanks The header tank breather is also connected into this breather ...

Page 24: ...e valid in both cases NOTE Flying 1 ball out of balance causes the fuel in the tanks to slosh in to one side by an angle of about 8 This leads to uneven fuel feeding 1 tank emptying before the other In extreme cases this can cause fuel starvation engine stoppage while there is significant fuel remaining in one wing tank Care must be taken to fly the aircraft in balance at all times CAUTION In the ...

Page 25: ...nstruments and radios The master bus powers all other electrical systems in addition to the instrument bus The master switch mounted on the lower left hand side of the instrument panel controls power to the main bus Another switch controls the connection between the main bus and the instrument bus The Master bus connects with the battery The feed from the alternator goes to the battery which acts ...

Page 26: ...tot probe mounted on the right wing strut Airspeed Indicator The airspeed indicator is calibrated in knots Limitations and range markings in KIAS are incorporated on the instrument Altimeter Aircraft altitude is depicted by a barometric type altimeter A knob near the lower left portion of the altimeter allows the ambient barometric pressure sub scale to be adjusted to the current value This sub sc...

Page 27: ...roaches the stall the angle of the airflow flowing past the lip produces a suction in the vent which sucks air through a reed squawker located in the wing root area of the cabin The squawker produces an audible note which increases in volume as the stall deepens The speed at which the warning activates is adjusted by changing the height of the lip below the vent on the wing and is set to go of 5 1...

Page 28: ...ment panel Electronic Flight Instrument System IRIS AV 10 EFIS The Jabiru J160 J170 Generation 1 and 2 instrument panels are fitted with either Option A or Option B components Option B panels come fitted with an EFIS unit as described below A larger glass cockpit display unit is fitted to Generation II Option B panels Figure 2 1 EFIS Unit Overview 1 SOFTKEY 1 POWER 2 BAROMETRIC PRESSURE TOGGLE KNO...

Page 29: ... AIRSPEED READOUT 7 ALTITUDE READOUT 8 WIND DIRECTION VELOCITY READOUT The EFIS ADI page is the default page when initialising the avionics systems on the J160 J170 Pressing Softkey 1 will power up the device when the Instrument Bus and Main Bus are powered Roll Scale The roll scale indicates degrees of bank in 10 20 30 and 45 increments Heading Readout The Heading readout displays the current mag...

Page 30: ...adjustment knob Left Mouse cycles the barometric pressure readout between inHG and Mb Increasing or decreasing the barometric pressure value is done using either the aircraft s altimeter adjustment knob or the barometric adjustment knob on the EFIS Wind speed and Direction Indicator The arrow shown will show the direction of the wind relative to the direction of the aircraft For example if the arr...

Page 31: ...nt coloured bars for the various conditions of flight and corresponds with the markers on the Airspeed Indicator Autopilot Annunciators The following annunciators display depending on the conditions of flight AP Autopilot engaged Vertical Hold Modes PIT Pitch hold engaged ALT Altitude hold engaged Lateral Hold Modes ROL Roll hold engaged HDG Heading hold engaged NAV NAV GPS hold engaged On initial...

Page 32: ...ewheel over the knob in ALT adjust mode flashing green light will adjust the autopilot selected altitude c Scrolling the mouse wheel over the knob when ALT and HDG adjust modes are not engaged static green light will adjust the autopilot vertical speed hold mode d Clicking the knob with the left mouse will set the vertical speed hold to zero or level flight 3 Heading Hold Mode a Press to engage he...

Page 33: ...hold mode 3 Press ALT again to engage altitude adjust mode 4 Use the Multi Function Knob to adjust the altitude value to 5 000ft 5 When the altitude mode reverts to altitude hold mode static green light use the Multi Function Knob to adjust your vertical speed component 6 When at the selected altitude the autopilot will cancel your climb and level off Turning to heading 090 degrees 1 Press AP to e...

Page 34: ...T KNOB 3 FREQUENCY DISPLAY Priority Switch Clicking this switch will set the Active COM frequency to guard of 121 500 Power Knob LEFT click this knob to power the unit up and RIGHT click this knob to turn the power off Frequency Display This LCD will display active and standby COM frequencies Frequency Swap Switch Clicking this switch will swap the current active and standby COM frequencies ...

Page 35: ...rently underlined Clicking this knob with the LEFT mouse button will toggle the user selectable standby frequency area between Mhz and Khz NAV RADIO Figure 3 2 NAV Radio 1 PRIORITY SWITCH 4 FREQUENCY SWAP SWITCH 2 POWER KNOB 5 FREQUENCY ADJUST KNOB 3 FREQUENCY DISPLAY Priority Switch This switch has no function Power Knob LEFT click this knob to power the unit up and RIGHT click this knob to turn ...

Page 36: ...es Frequency Swap Switch Clicking this switch will swap the current active and standby NAV frequencies Frequency Adjust Knob This knob tunes the standby frequency using the mouse wheel and will tune whichever frequency is currently underlined Clicking this knob with the LEFT mouse button will toggle the user selectable standby frequency area between Mhz and Khz ...

Page 37: ...TON 7 MODE KNOB 4 IDENT BUTTON 8 VFR BUTTON The Standby Mode shows your currently tuned Transponder frequency and does NOT transmit as indicated by the X on the left of the display The following buttons and knobs are common for all following Transponder modes and will only be described in this section Power Button This button turns the power to the unit on or off Mode Button This button is inactiv...

Page 38: ...tton is inactive Code Select Knob This knob allows you to increase or decrease your selected transponder digit from 0 7 using the mouse wheel Clicking the Knob with your LEFT mouse button will cycle through the first second third and fourth digit for adjustment Mode Knob This knob when clicked with the LEFT mouse button will cycle through the following four transponder modes Standby Mode STNBY Mod...

Page 39: ...o Mode A Operation 1 POWER BUTTON 5 CYCLE BUTTON 2 MODE BUTTON 6 CODE SELECT KNOB 3 ENTER BUTTON 7 MODE KNOB 4 IDENT BUTTON 8 VFR BUTTON When the Mode Knob is in the ON position the Transponder switches to Mode A operation and transmits the tuned transponder code as shown on the display A flashing R indicates transmission of the transponder ...

Page 40: ...ODE BUTTON 6 CODE SELECT KNOB 3 ENTER BUTTON 7 MODE KNOB 4 IDENT BUTTON 8 VFR BUTTON When the Mode knob is in the ALT position the Transponder switches to Mode A plus C operation and transmits the tuned transponder code as shown on the display In this mode the tuned barometric pressure in inches of mercury is shown below the transponder code A flashing R indicates transmission of the transponder ...

Page 41: ...CLE BUTTON 2 MODE BUTTON 6 CODE SELECT KNOB 3 ENTER BUTTON 7 MODE KNOB 4 IDENT BUTTON 8 VFR BUTTON When the Mode knob is in the ALT DISPLAY position the Transponder switches to Mode A plus C operation and transmits the tuned transponder code as shown on the display In this mode the pressure altitude in feet is shown below the transponder code A flashing R indicates transmission of the transponder ...

Page 42: ...TION 48 PREFLIGHT INSPECTION 49 Fuel 49 Cockpit 49 Left Undercarriage 50 Static Source 50 Empennage 50 Right Wing Trailing Edge 50 Right Wing 51 Nose 51 Pulling Through The Engine 51 Left Wing 52 Left Wing Trailing Edge 52 AMPLIFIED PROCEDURES 53 Before Starting Engine 53 Starting Engine Cold 53 Before Take Off 54 Ground Check and Run Up 54 Engine Management Ground Running 55 ...

Page 43: ...5 Pre Take Off 56 Warm Up 56 Power Check 56 Wing Flap and Power Settings 57 Take Off 57 Initial Climb 57 Enroute Climb 58 Cruise 58 Stalls 58 Descent 58 Before Landing and flight below 1000ft AGL 59 Approach and Landing 59 Landing 59 Cross Wind Landing 60 Baulked Landing 60 After Landing Securing 61 ...

Page 44: ...r a deviation exist SPEEDS FOR NORMAL OPERATION Unless otherwise noted the following speeds are based on a maximum weight of 540 kg 1190lb and may be used for any lesser weight Take Off T O S S Speed 50 ft 66 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 63 KIAS Baulked Landing 65 KIAS Initially Maxim...

Page 45: ...hecks of all undercarriage components tyres and brakes is warranted in these situations 1 Fuel Quantity in both tanks Check Fuel caps Secure Water Check Both tanks and header tank The fuel gauges used in the J160 J170 use a sender unit which has a built in analogue needle indicator for fuel level These senders are located in the wing roots and are visible to the crew These units may be used to con...

Page 46: ...t Harnesses Seats CHECK CONDITION Windshield CLEANLINESS Cockpit area GENERAL CONDITION Loose objects SECURE Cockpit Doors Latches CONDITION OPERATION Flight Manual AVAILABLE 3 Left Undercarriage Mount bolts CHECK SECURE Tyre CHECK CONDITION INFLATION 4 Static Source Static Source CHECK FOR BLOCKAGE 5 Empennage Tail tie down DISCONNECT Control surfaces CHECK Security Full Free Movement Rudder Elev...

Page 47: ... 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 Pulling Through The Engine 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 fel...

Page 48: ...gine 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 10 Left Wing Wing Tie Down DISCONNECT Wing Strut Mount Bolts CHECK Security Wing Root Mount Bolts CHECK Sec...

Page 49: ...f hand swinging or propping an engine when there is insufficient charge available in the aircraft battery for a normal start Starting using an external power source involves removing the upper engine cowl attaching jumper leads to the battery terminals and proceeding with the normal start sequence WARNING When the engine is started and battery charge restored shut down before re fitting the engine...

Page 50: ...ecs Choke Closed Throttle 900 1000 RPM Alternator Warning Light CHECK OFF Avionics ON 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...

Page 51: ... 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...

Page 52: ...ned and adjusted Oil temperature ABOVE 50 C Warm Up Most of the warm up will have occurred during taxiing and whilst conducting the Before Take Off checks The engine is warm enough for take off when the cylinder head and oil temperatures are in the green arcs Power Check Full throttle run ups over loose gravel are especially harmful to the propeller and should be avoided When take offs must be mad...

Page 53: ...flaps should not be retracted until a safe height is achieved and all obstacles have been cleared Take offs may be made with flaps up but this will increase the take off distance and will result in a more pronounced nose up attitude at lift off Take Off Carburettor heat OFF Throttle FULL OPEN Elevator Control NEUTRAL Directional Control NOSEWHEEL STEERING RUDDER Rotate 30 40 KIAS raise nose wheel ...

Page 54: ...ill result in increased range and endurance corresponding with the reduced fuel consumption At a power setting of 45 the J160 J170 is capable of attaining an endurance of close to 13 hours for a range of over 1000 nautical miles For efficient and economical operation as well as to achieve maximum engine service life the engine must always be operated in accordance with the procedures and specifica...

Page 55: ...roach speeds will result in prolonged floating and increased landing distance Normally the throttle should be fully closed during the flare to reduce the tendency to float and prolong the touchdown Touchdown should occur on the main wheels initially followed by the nose gear which should be held clear of the ground during the initial ground roll Positive braking may then be applied depending on re...

Page 56: ...ghtly nose high and wing low attitude touching down on the into wind mainwheel first followed by the other mainwheel and then the nose gear in quick succession In strong and or gusty wind conditions it may be desirable to make the final approach at a slightly higher than normal airspeed with partial or no flap selected Baulked Landing In a baulked landing go around the wing flaps should be retract...

Page 57: ... 0 0 1 A F M J A B I R U J 1 6 0 J 1 7 0 P a g e 57 FOR SIMULATION USE ONLY After Landing Securing Wing Flaps UP Fuel Pump OFF Parking Brake ON AS REQUIRED Avionics OFF Ignition OFF Master Switch OFF Controls SECURE ...

Page 58: ...63 APPROVED DATA 64 Airspeed Indicator System Calibration 64 Stall Speeds 64 Take Off Performance 65 Landing Distances 66 CLIMB 68 Best Rate of Climb Speed 68 Scheduled Climb 68 Take Off Configuration Climb 69 Landing Configuration Climb 70 CRUISE 70 Cruise Power Settings 70 Endurance 71 Baulked Landing Climb 71 Demonstrated Crosswind Performance 71 ...

Page 59: ...s Performance data is presented in tabular or graphical form to illustrate the effect of different variables Sufficiently detailed information is provided in the tables so that conservative values can be selected and used to determine the particular performance figure with reasonable accuracy Cruise performance data assumes that the aircraft is clean the engine is operating correctly and the prope...

Page 60: ... 0 J 1 7 0 P a g e 60 FOR SIMULATION USE ONLY APPROVED DATA Airspeed Indicator System Calibration Figure 4 1 Airspeed Indicator Calibration Chart NOTE Indicated airspeed assumes zero instrument error Stall Speeds Figure 4 2 Aircraft Stall Speeds ...

Page 61: ... from short dry grass increase the take off distance by 7 When taking off from soft ground or unusually long and or wet grass the take off distance will be even longer The pilot should therefore ensure that adequate strip length is available to cover these conditions The technique used in establishing the data in the take off distance table involves accelerating the aircraft along the ground with ...

Page 62: ...m landing distance for a variety of operating conditions The data is applicable when using a power off glide approach with the flaps extended to the Landing Flap or fully extended position and is based on landing distances from a height of 15 metre 50 feet to stop The landing distance is provided for a hard bitumen surface Wet and or slippery surfaces will increase the landing distance over that s...

Page 63: ... be no better than that appropriate to this lowest range The performance information is not valid when the outside air temperature and or pressure height exceeds the maximum values for which this information is scheduled Figure 4 4 Landing Distance For every 1 knot of head wind component the take off distance can be reduced by 11 meters For every 1 knot of tail wind component the take off distance...

Page 64: ...est Rate of Climb Speed The speed to obtain the best climb gradient when the flaps are fully retracted is 68 KIAS This speed does not vary with altitude Scheduled Climb Associated conditions Power Full Throttle Airspeed 71 KIAS Flaps UP Figure 4 5 Scheduled Climb Chart Take Off Configuration Climb ...

Page 65: ...I A P 2 0 2 0 0 0 1 A F M J A B I R U J 1 6 0 J 1 7 0 P a g e 65 FOR SIMULATION USE ONLY Associated conditions Power Full Throttle Airspeed 68 KIAS Flaps 17 Figure 4 6 Take Off Configuration Climb Chart ...

Page 66: ...g altitudes This feature has been examined by flight testing and verified for altitudes between sea level and 5000 ft Figure 4 7 Cruise Power Settings NOTE The JABIRU 2200 engine has an altitude compensating carburettor which provides for a fuel flow that is constant at all operating altitudes This feature has been examined by flight testing and verified for altitudes between sea level and 5000 ft...

Page 67: ...raph Cruise above When calculating endurance an allowance should be made for engine start taxi take off and climb In normal circumstances a total allowance of 5 litres for these would be adequate This allowance should be subtracted from the actual fuel on board prior to flight i e Fuel on Board Allowance Fuel assumed for endurance calculations Baulked Landing Climb Associated conditions Power Full...

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