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Jabiru J160 Product Manual

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FOR OFFICIAL USE ONLY
AIR PUBLICATION
2020.001-AFM
PRODUCT MANUAL
JABIRU J160/J70
Original Date of Issue: 1
October 2020
st
Software Version: v2.0.0
FOR SIMULATION USE ONLY

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Summary of Contents for Jabiru J160

  • Page 1 FOR OFFICIAL USE ONLY AIR PUBLICATION 2020.001-AFM PRODUCT MANUAL JABIRU J160/J70 Original Date of Issue: 1 October 2020 Software Version: v2.0.0 FOR SIMULATION USE ONLY...
  • Page 2 Instructions in this manual are for a pilot inexperienced in the operation of the simulation aircraft. APPLICABILITY This Flight Manual applies to the Jabiru J-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.
  • Page 3 J A B I R U J 1 6 0 / J 1 7 0 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e AMENDMENT ACTION To assist in the maintaining of this publication in an up-to-date condition, users are to bring to the notice of IRIS Flight Simulation Software, any errors, omissions or suggestions for improvement by email to help@irissimulations.com.au.
  • Page 4 J A B I R U J 1 6 0 / J 1 7 0 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e CONTROL AND IDENTIFICATION MARKINGS The use of block capitals in the text, when identifying switches, controls etc. indicates the actual markings on that item.
  • Page 5 J A B I R U J 1 6 0 / J 1 7 0 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e TACTILE OPERATION Whilst it is important to have a joystick or yoke along with a throttle to get the best out of your simulation experience, it is ESSENTIAL that you have a mouse with a scrollable mouse-wheel in order to interact fully with the items inside the simulation’s virtual cockpit.
  • Page 6 J A B I R U J 1 6 0 / J 1 7 0 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e LIST OF ASSOCIATED PUBLICATIONS IAP 2020.001-ACL1 Abbreviated Checklists IAP 2020.001-PA Product Acknowledgements...
  • Page 7 J A B I R U J 1 6 0 / J 1 7 0 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e TABLE OF CONTENTS Page No SECTION 1 DESCRIPTION AND OPERATION SECTION 2...

  • Page 8: Table Of Contents

    J A B I R U J 1 6 0 / J 1 7 0 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e SECTION 1 DESCRIPTION AND OPERATION TABLE OF CONTENTS Page No CHAPTER 1 DESCRIPTION AND OPERATION - GENERAL...
  • Page 9 J A B I R U J 1 6 0 / J 1 7 0 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Ignition System Starting System Air Induction System Exhaust System Cooling System GROUND CONTROL...
  • Page 10 J A B I R U J 1 6 0 / J 1 7 0 | 10 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e STALL WARNING SYSTEM AVIONICS Electronic Flight Instrumentation System ADI Page...

  • Page 11: Chapter 1 Description And Operation - General

    DESCRIPTION AND OPERATION - GENERAL THE AIRCRAFT Introduction The J160/J170 aircraft is a strut braced, high wing, fixed tricycle undercarriage, single engine, two seat aircraft that has been designed primarily for training and recreational operations. The fuselage, wings and empennage are constructed from composite materials.

  • Page 12: Dimensions

    I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Figure 1-1 Jabiru J160/J170 General Arrangement Dimensions The overall dimensions of the aircraft with normal tire and strut inflation are shown in Figure 1-2.

  • Page 13: Airframe

    J A B I R U J 1 6 0 / J 1 7 0 | 13 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Figure 1-2 Aircraft Dimensions AIRFRAME Wings The wings are of GRP skin construction, and are externally braced with a...

  • Page 14: Flight Controls

    Adjustable Rudder Pedals J160/J170 aircraft have the option of fitting adjustable rudder pedals. These pedals have two positions, in and out. To adjust the pedals pull the ring on the side of the pedals to the side to release the pedal face. Move the pedal face to the desired location (in or out).

  • Page 15: Instrument Panel

    J A B I R U J 1 6 0 / J 1 7 0 | 15 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e INSTRUMENT PANEL Although the instrument panel spans the width of the cockpit, flight instruments are on the left hand side in front of the pilot.
  • Page 16 In all aircraft, the core elements shown above are included, though layout may vary depending on the aircraft and panel configuration. Generally, J160 aircraft will feature the Generation 1 Panel, and the J170, the Generation II panel, either with analogue or digital displays.

  • Page 17: Engine

    Figure 1-4 Jabiru J2200 4 Cylinder Engine The engine is a four cylinder, horizontally opposed, air cooled, naturally aspirated Jabiru 2200B or 2200C, fitted with an altitude compensating carburettor. Both engines are rated by the manufacturer to 80 BHP at full throttle and 3300 RPM.

  • Page 18: Auto Mixture System

    I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Auto Mixture System The Jabiru J2200 engine has an auto mixture system and a manual choke. To simulate this system within the boundaries of Microsoft Flight Simulator a system is incorporated which operates as follows;...

  • Page 19: Ignition System

    J A B I R U J 1 6 0 / J 1 7 0 | 19 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e An oil filler cap/dipstick is located on the top of the engine and is accessible through an access door in the engine cowling.

  • Page 20: Air Induction System

    J A B I R U J 1 6 0 / J 1 7 0 | 20 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Air Induction System The engine induction air normally enters through a NACA duct on the left side of the lower engine cowl.

  • Page 21: Ground Control

    P a g e GROUND CONTROL The J160/J170 is fitted with mechanical linkage from the rudder pedals to the nose wheel. This gives ground steering control. The minimum turning radius is approximately 5m (or approximately 1m outboard of the wingtip).

  • Page 22: Seats

    I A P 2 0 2 0 . 0 0 1 - A F M / P a g e SEATS Seats in the J160/J170 are an integral part of the moulded structure. The seat base contains foam which is designed to crush in the event of an accident, absorbing energy from large vertical decelerations.

  • Page 23: Fuel System

    J A B I R U J 1 6 0 / J 1 7 0 | 23 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e FUEL SYSTEM The aircraft has a fuel tank in the inboard section of each wing, and a small header tank which is located in a sealed compartment underneath the baggage shelf.

  • Page 24: Brake System

    This system ensures that the air space pressure in each tank is the same, minimising uneven fuel feed rates. The J160/J170 may use either two fuel sight gauges (one in each wing root) or two electric fuel gauges on the instrument panel to show fluid levels in each wing tank.

  • Page 25: Electrical System

    • Check park brake is OFF prior to landing. ELECTRICAL SYSTEM The J160/J170 has a 12 volt electrical system consisting of a 12 volt battery, starter motor, regulator, alternator with a nominal 14 volt output, electric flap, electric fuel boost pump, circuit breakers, oil temperature gauge, optional strobe lights, switches and related wiring.

  • Page 26: Cockpit Ventilation

    J A B I R U J 1 6 0 / J 1 7 0 | 26 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e COCKPIT VENTILATION Ventilation air is provided by vents located beside the rudder pedals. The volume of the air supply can be regulated by sliding the vent shutters as desired using your foot.
  • Page 27 J A B I R U J 1 6 0 / J 1 7 0 | 27 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e STALL WARNING SYSTEM The aircraft is equipped with an air operated artificial stall warning system.
  • Page 28 ON the Master and Instrument Switches on the instrument 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.
  • Page 29 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.
  • Page 30 J A B I R U J 1 6 0 / J 1 7 0 | 30 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Roll Pointer The roll pointers show orientation of the aircraft in relation to the roll scale. Vertical Speed Scale The vertical speed scale shows the value relating to the deviation of the pink vertical speed bar (not shown).
  • Page 31 J A B I R U J 1 6 0 / J 1 7 0 | 31 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Aircraft Reference Symbol The aircraft reference symbol displays a visual indication of the aircraft relative to the artificial horizon, pitch ladder and roll reference scale.
  • Page 32 Available in the J160/J170 Option B panel, the AMCP provides pilot interaction with the autopilot on the aircraft. Regardless of the J160 or the J170, the functionality remains the same. From Left to Right, the functions are as follows; 1. Autopilot Master pushbutton a.
  • Page 33 J A B I R U J 1 6 0 / J 1 7 0 | 33 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Note: If the multi-function knob is not used within 2 seconds of entering heading or altitude adjust mode, the system will revert to heading or altitude hold mode.
  • Page 34 J A B I R U J 1 6 0 / J 1 7 0 | 34 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e COM RADIO Figure 3-1 COM Radio 1.
  • Page 35 J A B I R U J 1 6 0 / J 1 7 0 | 35 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Frequency Adjust Knob This knob tunes the standby frequency using the mouse-wheel, and will tune whichever frequency is currently underlined.
  • Page 36 J A B I R U J 1 6 0 / J 1 7 0 | 36 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Frequency Display This LCD will display active and standby NAV frequencies. Frequency Swap Switch Clicking this switch will swap the current active and standby NAV frequencies.
  • Page 37 J A B I R U J 1 6 0 / J 1 7 0 | 37 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e TRANSPONDER RADIO – STANDBY MODE Figure 3-2 Transponder Radio –...
  • Page 38 J A B I R U J 1 6 0 / J 1 7 0 | 38 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e IDENT Button This button sets your Transponder to IDENT mode and squawks IDENT for a short period of time.
  • Page 39 J A B I R U J 1 6 0 / J 1 7 0 | 39 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e TRANSPONDER RADIO – MODE A Figure 3-2 Transponder Radio –...
  • Page 40 J A B I R U J 1 6 0 / J 1 7 0 | 40 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e TRANSPONDER RADIO – MODE A & C Figure 3-2 Transponder Radio –...
  • Page 41 J A B I R U J 1 6 0 / J 1 7 0 | 41 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e TRANSPONDER RADIO – MODE A & C (With Altitude) Figure 3-2 Transponder Radio –...
  • Page 42 J A B I R U J 1 6 0 / J 1 7 0 | 42 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e SECTION 2 NORMAL OPERATIONS TABLE OF CONTENTS Page No GENERAL...
  • Page 43 J A B I R U J 1 6 0 / J 1 7 0 | 43 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Taxiing Pre Take-Off Warm Up Power Check Wing Flap and Power Settings...

  • Page 44: General

    J A B I R U J 1 6 0 / J 1 7 0 | 44 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e SECTION 2 CHAPTER 1 NORMAL OPERATIONS GENERAL The procedures are arranged in the sequence considered to be the most...

  • Page 45: Preflight Inspection

    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.

  • Page 46: Left Undercarriage

    J A B I R U J 1 6 0 / J 1 7 0 | 46 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Alternator Warning Light CONFIRM ON Before Start Master Switch Aileron and elevator cables &...

  • Page 47: Right Wing

    J A B I R U J 1 6 0 / J 1 7 0 | 47 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Flap CHECK Security Control rods &...

  • Page 48: Left Wing

    • 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.

  • Page 49: Amplified Procedures

    CHECK OPERATION using test switch The Jabiru 2200 engine is fitted with a dual electronic ignition system. The engine will not start below 300 RPM, which precludes the option of hand swinging or "propping" an engine when there is insufficient charge available in the aircraft battery for a normal start.

  • Page 50: Before Take-Off

    J A B I R U J 1 6 0 / J 1 7 0 | 50 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Ignition switches Starter ENGAGE when engine fires RELEASE** Oil Pressure...

  • Page 51: Engine Management - Ground Running

    P a g e Engine Management - Ground Running The 2200 engine fitted to the J160/J170 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.

  • Page 52: Pre Take-Off

    J A B I R U J 1 6 0 / J 1 7 0 | 52 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Pre Take-Off Master Switch Ignition switches BOTH ON Fuel Shutoff Valve...

  • Page 53: Wing Flap And Power Settings

    J A B I R U J 1 6 0 / J 1 7 0 | 53 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Any sign of rough engine operation or sluggish acceleration is good cause for discontinuing the take-off and conducting a full power run-up to confirm normal engine operation prior to the next take-off attempt.

  • Page 54: Enroute Climb

    Power settings below this will 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.

  • Page 55: Before Landing (And Flight Below 1000Ft Agl)

    J A B I R U J 1 6 0 / J 1 7 0 | 55 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Before Landing (and flight below 1000ft AGL) Brakes Harnesses SECURE...

  • Page 56: Cross Wind Landing

    @ 50ft to 68 KIAS Cross Wind Landing The J160/J170 has been approved for operations in crosswinds of up to 14 Knots. When landing in a strong cross wind use a wing low, crab, or a combination method of drift correction.

  • Page 57: After Landing/Securing

    J A B I R U J 1 6 0 / J 1 7 0 | 57 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e After Landing/Securing Wing Flaps Fuel Pump Parking Brake ON/AS REQUIRED...
  • Page 58 J A B I R U J 1 6 0 / J 1 7 0 | 58 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e SECTION 3 PERFORMANCE DATA TABLE OF CONTENTS Page No GENERAL...

  • Page 59: General

    J A B I R U J 1 6 0 / J 1 7 0 | 59 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e SECTION 3 CHAPTER 1 PERFORMANCE DATA GENERAL The performance data on the following pages is presented so that you may...

  • Page 60: Approved Data

    J A B I R U J 1 6 0 / J 1 7 0 | 60 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e APPROVED DATA Airspeed Indicator System Calibration Figure 4-1 Airspeed Indicator Calibration Chart NOTE •...

  • Page 61: Take-Off Performance

    J A B I R U J 1 6 0 / J 1 7 0 | 61 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e NOTE • Stalling speeds will reduce as weight is reduced. •...

  • Page 62: Landing Distances

    J A B I R U J 1 6 0 / J 1 7 0 | 62 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e 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.
  • Page 63 J A B I R U J 1 6 0 / J 1 7 0 | 63 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e When the outside air temperature and/or pressure height is below the lowest range scheduled on the charts, the aircraft performance shall be assumed to be no better than that appropriate to this lowest range.

  • Page 64: Climb

    J A B I R U J 1 6 0 / J 1 7 0 | 64 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e CLIMB Best Rate of Climb Speed The speed to obtain the best climb gradient when the flaps are fully retracted is 68 KIAS.
  • Page 65 J A B I R U J 1 6 0 / J 1 7 0 | 65 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e Associated conditions: Power: Full Throttle Airspeed: 68 KIAS Flaps: 17° Figure 4-6 Take-Off Configuration Climb Chart FOR SIMULATION USE ONLY...

  • Page 66: Landing Configuration Climb

    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.

  • Page 67: Endurance

    J A B I R U J 1 6 0 / J 1 7 0 | 67 I A P 2 0 2 0 . 0 0 1 - A F M / P a g e • For flight planning purposes when the flight is above 5,000 ft., pilots should program a fuel burn which is for the next highest rpm range in the table above.

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