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OVERHAUL MANUAL
FOR
JABIRU 2200 & 3300 AIRCRAFT ENGINES
DOCUMENT No. JEM0001-8
Date: 8th July 2015
This Manual has been prepared as a guide to correctly overhaul Jabiru 2200 & 3300 aero engines.
It is the owner's responsibility to regularly check the Jabiru web site at www.jabiru.net.au for
applicable Service Bulletins and have them implemented as soon as possible. Manuals are also
updated periodically with the latest revisions available from the web site. Failure to maintain the
engine or aircraft with current service information may render the aircraft un-airworthy and void
Jabiru’s Limited, Express Warranty.
This document is controlled while it remains on the Jabiru server. Once this no longer applies the
document becomes uncontrolled.
Should you have any questions or doubts about the contents of this manual, please contact Jabiru
Aircraft Pty Ltd.
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Engine Overhaul Manual
JEM0001-8
1.1
1.2
2
Jabiru 2200 & 3300 Aircraft Engines
TABLE OF FIGURES .................................................................................................................................................................. 7
TABLE OF TABLES.................................................................................................................................................................. 11
GENERAL INFORMATION .................................................................................................................................................. 12
2.1
2.2
2.3
2.4
2.5
2.6
2.7
2.8
2.9
2.10
2.11
2.12
2.13
LIST OF EFFECTIVE PAGES / ISSUE STATUS ................................................................................................................................. 12
INTRODUCTION .................................................................................................................................................................... 13
APPLICABILITY ...................................................................................................................................................................... 13
CERTIFICATION BASIS ............................................................................................................................................................ 13
READING THIS MANUAL ........................................................................................................................................................ 14
DEGREE OF DIFFICULTY .......................................................................................................................................................... 14
MANUAL LAYOUT ................................................................................................................................................................. 14
ENGINE LIFE......................................................................................................................................................................... 14
COMPLETE OVERHAUL, TOP END OVERHAUL, WEAR TOLERANCES.................................................................................................... 15
MANDATORY UPDATES .......................................................................................................................................................... 15
MANDATORY REPLACEMENT OF PARTS ...................................................................................................................................... 15
RECORDING ......................................................................................................................................................................... 15
GENERAL DESCRIPTION .......................................................................................................................................................... 16
2.13.1
2.13.2
2.13.3
2.13.4
2.13.5
2.13.6
2.13.7
2.13.8
2.13.9
2.13.10
2.13.11
2.13.12
2.13.13
2.13.14
2.13.15
2.13.16
2.13.17
2.13.18
2.13.19
2.13.20
2.13.21
2.13.22
2.13.23
2.14
3
Jabiru Aircraft Pty Ltd
Engine identification ...................................................................................................................................................................17
Build Configurations ...................................................................................................................................................................17
Part Identification ....................................................................................................................................................................... 17
Cylinder Numbering Convention ................................................................................................................................................. 17
Cylinder heads ............................................................................................................................................................................ 17
Valves, valve guides and seats .................................................................................................................................................... 17
Cylinders ..................................................................................................................................................................................... 18
Pistons ........................................................................................................................................................................................ 18
Connecting rods .......................................................................................................................................................................... 18
Crankshaft .................................................................................................................................................................................. 18
Crankcase ................................................................................................................................................................................... 18
Camshaft .................................................................................................................................................................................... 18
Valve operating mechanism ....................................................................................................................................................... 18
Solid lifters .................................................................................................................................................................................. 18
Hydraulic lifters........................................................................................................................................................................... 18
Roller Followers .......................................................................................................................................................................... 18
Lubricating system ...................................................................................................................................................................... 18
Cooling system ............................................................................................................................................................................ 19
Induction system ......................................................................................................................................................................... 19
Ignition system ........................................................................................................................................................................... 19
Electrical charging system .......................................................................................................................................................... 19
Starter motor .............................................................................................................................................................................. 19
Sump ........................................................................................................................................................................................... 19
ASSESSING AN ENGINE .......................................................................................................................................................... 19
GENERAL OVERHAUL PROCEDURES ................................................................................................................................. 20
3.1
3.2
3.3
3.4
3.4.1
3.4.2
3.4.3
3.5
3.6
3.6.1
3.6.2
3.6.3
3.6.4
3.7
3.7.1
3.7.2
3.7.3
3.7.4
MANUAL LAYOUT ................................................................................................................................................................. 20
DIRECTIONAL REFERENCES ..................................................................................................................................................... 20
TOP END OVERHAUL VS FULL OVERHAUL .................................................................................................................................. 20
SPECIAL CLASSES OF OVERHAUL .............................................................................................................................................. 20
Bulk Strip ......................................................................................................................................................................................... 20
Propeller strike procedures .............................................................................................................................................................. 21
Abrupt Engine Stoppage ..................................................................................................................................................................22
SEQUENCE OF EVENTS ........................................................................................................................................................... 22
MAINTAINER REQUIREMENTS ................................................................................................................................................. 23
Facilities ........................................................................................................................................................................................... 23
Training ........................................................................................................................................................................................... 23
Rating .............................................................................................................................................................................................. 23
Experience ....................................................................................................................................................................................... 23
OVERHAUL TOOLS & EQUIPMENT ............................................................................................................................................ 23
Tool & Gauge Control ...................................................................................................................................................................... 23
Tools: ............................................................................................................................................................................................... 23
Equipment: ...................................................................................................................................................................................... 23
General: ........................................................................................................................................................................................... 24
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3.7.5
3.8
4
Recommended Sealants Compounds & Lubricants.......................................................................................................................... 25
Special Tools .................................................................................................................................................................................... 28
Torque / Tension Wrench ................................................................................................................................................................ 36
Torque Application Procedure ......................................................................................................................................................... 37
SAFETY WIRE....................................................................................................................................................................... 38
HARDWARE ......................................................................................................................................................................... 39
DISASSEMBLY PROCEDURE .............................................................................................................................................. 40
4.1
4.2
4.3
4.4
PRELIMINARY CLEANING ........................................................................................................................................................ 40
REMOVE THE ENGINE FROM THE AIRCRAFT............................................................................................................................... 40
ENGINE STAND .................................................................................................................................................................... 40
SPECIAL CHECKS BEFORE DISASSEMBLY..................................................................................................................................... 41
4.4.1
4.4.2
4.5
In-Situ Propeller Flange & Crankshaft Run-Out Measurement ........................................................................................................ 41
Engine Through-Bolt Check.............................................................................................................................................................. 41
ENGINE STRIP: COMPLETE OVERHAUL ...................................................................................................................................... 42
4.5.1
4.5.2
4.5.3
4.5.4
4.5.5
4.5.6
4.5.7
4.5.8
4.5.9
4.5.10
4.5.11
4.5.12
4.5.13
4.5.14
4.5.15
4.5.16
4.5.17
4.5.18
4.5.19
4.5.20
4.5.21
4.6
4.6.1
4.6.2
4.6.3
4.6.4
4.6.5
4.6.6
4.6.7
4.6.8
5
Jabiru 2200 & 3300 Aircraft Engines
LOCTITE 620 & OTHER RETAINING COMPOUNDS ....................................................................................................................... 27
3.8.1
3.8.2
3.8.3
3.9
3.10
Jabiru Aircraft Pty Ltd
Accessories ...................................................................................................................................................................................... 42
Cylinder Heads And Valve Gear ....................................................................................................................................................... 42
Cam Followers, Rocker Oil Lines ...................................................................................................................................................... 42
Flywheel Cap Screws ........................................................................................................................................................................ 43
Distributor Drive Housings ............................................................................................................................................................... 43
Flywheel........................................................................................................................................................................................... 44
Timing Case ..................................................................................................................................................................................... 44
Engine Mount Plate And Sump ........................................................................................................................................................ 45
Starter Motor................................................................................................................................................................................... 45
Crankshaft Gear .......................................................................................................................................................................... 46
Cylinders ..................................................................................................................................................................................... 46
Pistons ........................................................................................................................................................................................ 47
Front Seal & Oil Pump Housings ................................................................................................................................................. 47
Oil Return Manifolds ...................................................................................................................................................................48
Roller Follower Locking Plate ...................................................................................................................................................... 48
Crankcase ................................................................................................................................................................................... 49
Oil Pickup Tube And Strainer....................................................................................................................................................... 50
Camshaft And Cam Followers ..................................................................................................................................................... 50
Connecting rods .......................................................................................................................................................................... 50
Crankshaft .................................................................................................................................................................................. 51
Group The Parts .......................................................................................................................................................................... 51
ENGINE STRIP: TOP END OVERHAUL ........................................................................................................................................ 52
Accessories ...................................................................................................................................................................................... 52
Cylinder Heads And Valve Gear ....................................................................................................................................................... 52
Cylinders .......................................................................................................................................................................................... 52
Pistons ............................................................................................................................................................................................. 52
Connecting Rods .............................................................................................................................................................................. 52
Flywheel & Gear Case ...................................................................................................................................................................... 52
Propeller Flange ............................................................................................................................................................................... 52
Group The Parts ............................................................................................................................................................................... 52
INSPECTION AND ASSESSMENT ........................................................................................................................................ 53
5.1
5.2
5.3
5.4
5.5
5.6
5.7
5.7.1
5.7.2
5.7.3
5.8
5.8.1
5.8.2
5.8.3
MANDATORY REPLACEMENT ITEMS – MULTI-CYCLE PARTS .......................................................................................................... 53
MANDATORY REPLACEMENT ITEMS – FULL OVERHAUL ................................................................................................................ 53
MANDATORY REPLACEMENT ITEMS – TOP END OVERHAUL .......................................................................................................... 54
GENERAL ............................................................................................................................................................................ 55
MANDATORY UPDATES .......................................................................................................................................................... 55
MANDATORY DISCARD .......................................................................................................................................................... 55
CLEANING ........................................................................................................................................................................... 56
Materials and Processes ..................................................................................................................................................................56
Degreasing....................................................................................................................................................................................... 56
Removal of hard carbon ..................................................................................................................................................................56
INSPECTION ......................................................................................................................................................................... 57
Return to service repair work .......................................................................................................................................................... 57
High temperature operation............................................................................................................................................................ 57
Bearing surfaces .............................................................................................................................................................................. 57
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5.8.4
5.8.5
5.8.6
5.8.7
5.8.8
5.9
SUBASSEMBLY A – CRANKSHAFT, PROPELLER FLANGE AND CONNECTING RODS ................................................................................. 59
Crankshaft and propeller flange ...................................................................................................................................................... 59
Connecting rods ............................................................................................................................................................................... 61
SUBASSEMBLY B – CRANKCASE, CAMSHAFT AND OIL PUMP ........................................................................................................... 63
5.10.1
5.10.2
5.10.3
5.10.4
5.10.5
5.11
Exhaust System ........................................................................................................................................................................... 97
ASSEMBLY – TOP-END OVERHAUL ................................................................................................................................... 98
6.1
6.2
6.3
7
Carburettor ................................................................................................................................................................................. 93
Fuel Pump ................................................................................................................................................................................... 96
SUBASSEMBLY H – FINAL ASSEMBLY ........................................................................................................................................ 97
5.16.1
6
Gear Case & Distributors ............................................................................................................................................................ 91
SUBASSEMBLY G – FUEL PUMP AND CARBURETTOR.................................................................................................................... 93
5.15.1
5.15.2
5.16
Ignition Coils & Alternator .......................................................................................................................................................... 87
Flywheel/Starfish Attachment .................................................................................................................................................... 88
Starter Motor .............................................................................................................................................................................. 88
Engine Mount Plate .................................................................................................................................................................... 90
SUBASSEMBLY F – GEAR CASE AND DISTRIBUTORS....................................................................................................................... 91
5.14.1
5.15
Sump ........................................................................................................................................................................................... 84
Induction Manifold ..................................................................................................................................................................... 86
SUBASSEMBLY E – FLYWHEEL, IGNITION COILS, STARTER MOTOR AND ALTERNATOR ........................................................................ 87
5.13.1
5.13.2
5.13.3
5.13.4
5.14
Pistons and cylinders ..................................................................................................................................................................72
Cylinder heads ............................................................................................................................................................................ 74
Valves ......................................................................................................................................................................................... 75
Valve guides ................................................................................................................................................................................ 77
Valve seats .................................................................................................................................................................................. 79
Cylinder Head – Cylinder Seal ..................................................................................................................................................... 81
Valve Springs, Spring Washers & Pushrods.................................................................................................................................81
Rockers ....................................................................................................................................................................................... 83
SUBASSEMBLY D – SUMP & INDUCTION MANIFOLD .................................................................................................................... 84
5.12.1
5.12.2
5.13
Crankcase ................................................................................................................................................................................... 63
Hydraulic Valve Lifters ................................................................................................................................................................ 66
Camshaft .................................................................................................................................................................................... 67
Oil pump ..................................................................................................................................................................................... 69
Oil Pressure Relief Valve ............................................................................................................................................................. 70
SUBASSEMBLY C – PISTONS, CYLINDERS AND CYLINDER HEADS....................................................................................................... 72
5.11.1
5.11.2
5.11.3
5.11.4
5.11.5
5.11.6
5.11.7
5.11.8
5.12
Jabiru 2200 & 3300 Aircraft Engines
Gears ............................................................................................................................................................................................... 57
Corrosion on stressed areas ............................................................................................................................................................. 57
Magnetic particle inspection (MPI).................................................................................................................................................. 58
Damaged parts ................................................................................................................................................................................ 58
Replacement of studs or broken cap screws .................................................................................................................................... 58
5.9.1
5.9.2
5.10
Jabiru Aircraft Pty Ltd
GENERAL ............................................................................................................................................................................ 98
ENGINE THROUGH-BOLTS ...................................................................................................................................................... 98
FUEL PUMP ......................................................................................................................................................................... 98
ASSEMBLY – FULL OVERHAUL .......................................................................................................................................... 99
7.1
7.1.1
7.1.2
7.1.3
7.2
7.2.1
7.2.2
7.3
7.3.1
7.3.2
7.3.3
7.3.4
7.4
7.5
7.5.1
7.5.2
7.5.3
SUBASSEMBLY A – CRANKSHAFT, PROPELLER FLANGE AND CONNECTING RODS ............................................................................... 100
Crankshaft, propeller flange .......................................................................................................................................................... 100
Connecting rods ............................................................................................................................................................................. 101
Assemble ....................................................................................................................................................................................... 102
SUBASSEMBLY B – CRANKCASE AND CAMSHAFT........................................................................................................................ 104
Crankcase ...................................................................................................................................................................................... 104
Camshaft ....................................................................................................................................................................................... 107
SUBASSEMBLY C – PISTONS, CYLINDERS AND CYLINDER HEADS..................................................................................................... 108
Pistons ........................................................................................................................................................................................... 108
Cylinders ........................................................................................................................................................................................ 113
Through-Bolt Nuts ......................................................................................................................................................................... 114
Cylinder heads ............................................................................................................................................................................... 115
SUBASSEMBLY D – SUMP ..................................................................................................................................................... 117
SUBASSEMBLY E – FLYWHEEL, IGNITION COILS, STARTER MOTOR AND ALTERNATOR ...................................................................... 118
Ignition Coils .................................................................................................................................................................................. 118
Alternator ...................................................................................................................................................................................... 118
Flywheel......................................................................................................................................................................................... 118
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7.5.4
7.6
Starter Motor................................................................................................................................................................................. 119
Engine Mount Plate & Tacho Pickup .............................................................................................................................................. 120
Distributor Case & Distributor Mounts .......................................................................................................................................... 121
SUBASSEMBLY G – FUEL PUMP AND CARBURETTOR.................................................................................................................. 123
7.7.1
7.7.2
7.8
Carburettor .................................................................................................................................................................................... 123
Fuel Pump ...................................................................................................................................................................................... 123
SUBASSEMBLY H – FINAL ASSEMBLY ....................................................................................................................................... 124
7.8.1
7.8.2
7.8.3
7.8.4
7.8.5
7.8.6
7.8.7
7.8.8
7.8.9
7.8.10
7.8.11
7.8.12
7.8.13
7.8.14
7.8.15
7.8.16
7.8.17
7.8.18
8
Crankcase Joining .......................................................................................................................................................................... 124
Option – Fitting Oil Pump .............................................................................................................................................................. 129
Setting Cam Timing ....................................................................................................................................................................... 130
Sump .............................................................................................................................................................................................. 132
Engine Mount Plate ....................................................................................................................................................................... 134
Distributor drives ........................................................................................................................................................................... 136
Flywheel and Alternator Rotor ...................................................................................................................................................... 138
Ignition Posts & Alternator Stator ................................................................................................................................................. 140
Distributor Caps ............................................................................................................................................................................. 141
Cylinder Heads .......................................................................................................................................................................... 142
Induction Plenum & Tubes ........................................................................................................................................................ 146
Exhaust Pipes ............................................................................................................................................................................ 148
Carburettor ............................................................................................................................................................................... 148
High-Tension Leads & Spark Plugs ............................................................................................................................................ 148
Front Crankshaft Seal Housing.................................................................................................................................................. 149
Propeller Flange ........................................................................................................................................................................ 150
Oil pump ................................................................................................................................................................................... 152
Oil Pressure Relief Valve ........................................................................................................................................................... 153
POST-ASSEMBLY ............................................................................................................................................................ 155
8.1
8.2
8.3
8.4
8.5
9
Jabiru 2200 & 3300 Aircraft Engines
SUBASSEMBLY F – GEAR CASE AND DISTRIBUTORS..................................................................................................................... 120
7.6.1
7.6.2
7.7
Jabiru Aircraft Pty Ltd
OILS................................................................................................................................................................................. 155
BEFORE FIRST START ........................................................................................................................................................... 155
GROUND RUN-IN & TEST PROCEDURES .................................................................................................................................. 156
FINAL TASKS ...................................................................................................................................................................... 157
TROUBLESHOOTING ............................................................................................................................................................ 158
APPENDIX A - BUILD SHEETS & TEST CARDS – APPROVED SECTION ................................................................................ 160
9.1
TORQUE SETTINGS .............................................................................................................................................................. 160
9.1.1
9.2
9.3
9.4
9.5
Table of Torque Specifications ....................................................................................................................................................... 160
BUILD TOLERANCES............................................................................................................................................................. 161
MULTI-CYCLE ITEMS ........................................................................................................................................................... 162
COMPOUNDS & SEALANTS ................................................................................................................................................... 162
MAXIMUM ALLOWABLE CLEARANCES (WEAR LIMITS) ............................................................................................................... 163
9.5.1
9.6
9.7
Oil Pump Clearance Measurement: ............................................................................................................................................... 164
ELECTRICAL SYSTEM SPECIFICATIONS ...................................................................................................................................... 164
DISASSEMBLY RECORD SHEET ............................................................................................................................................... 166
9.7.1
9.7.2
9.8
9.9
Engine Details ................................................................................................................................................................................ 166
Engine Disassembly Record Sheet ................................................................................................................................................. 166
SAMPLE COMPLETED BUILD SHEET ........................................................................................................................................ 167
JABIRU ENGINE BUILD BOOKLET ............................................................................................................................................ 167
9.9.1
9.9.2
9.9.3
9.9.4
9.9.5
9.9.6
9.9.7
9.9.8
9.9.9
9.9.10
9.9.11
9.10
Engine Details ................................................................................................................................................................................ 167
Subassembly A Build Sheet – Crankshaft, Propeller Mount Flange and Conrods .......................................................................... 168
Subassembly B Build Sheet – Crankcase and Camshaft Assembly .................................................................................................169
Subassembly C Build Sheet – Pistons, Cylinders and Cylinder Heads ............................................................................................. 170
Subassembly D Build Sheet – Sump ............................................................................................................................................... 171
Subassembly E Build Sheet – Flywheel, Ignition Coils, Starter Motor And Alternator .................................................................... 171
Subassembly F Build Sheet – Gear Case......................................................................................................................................... 172
Subassembly G – Fuel Pump and Carburettor ............................................................................................................................... 173
Subassembly H – Final Assembly ................................................................................................................................................... 174
Ground Run-In Procedure ......................................................................................................................................................... 175
Jabiru Engine Build: Parts Measure and Clearance Record Sheet ............................................................................................. 177
TOP END OVERHAUL BOOKLET .............................................................................................................................................. 178
9.10.1
9.10.2
Engine Details ........................................................................................................................................................................... 178
Top End Subassembly A Build Sheet – Conrods ......................................................................................................................... 178
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9.10.3
9.10.4
9.10.5
9.10.6
9.10.7
9.10.8
9.10.9
9.10.10
10
Bulk Strip Checklist.................................................................................................................................................................... 186
JOB SUMMARY SHEET ......................................................................................................................................................... 187
APPENDIX C - WEAR FACTORS ........................................................................................................................................ 188
11.1
WEAR FACTORS ................................................................................................................................................................. 188
APPENDIX D - MANDATORY REPLACEMENT PARTS ........................................................................................................ 189
12.1
12.2
12.3
GENERAL .......................................................................................................................................................................... 189
CAMSHAFT ........................................................................................................................................................................ 190
CRANKCASE ....................................................................................................................................................................... 190
12.3.1
12.3.2
12.3.3
12.4
Maximum Surfacing / Decking Limit ......................................................................................................................................... 190
Fretting General Information .................................................................................................................................................... 191
Fretted Crankcase Repair .......................................................................................................................................................... 191
CRANKSHAFT ..................................................................................................................................................................... 193
12.4.1
12.4.2
13
Top End Subassembly C Build Sheet – Pistons, Cylinders and Cylinder Heads........................................................................... 179
Top End Subassembly E Build Sheet – Starter Motor ................................................................................................................ 179
Top End Subassembly F Build Sheet – Gear Case ...................................................................................................................... 180
Top End Subassembly G – Fuel Pump and Carburettor ............................................................................................................. 181
Top End Subassembly H – Final Assembly .................................................................................................................................182
Top End – Engine Ground Run-In Procedure ............................................................................................................................. 182
Top End – Engine Post Run Procedure – Stage J ....................................................................................................................... 182
Parts Measure and Clearance Record Sheet ............................................................................................................................. 183
JOB TRAVELLER .................................................................................................................................................................. 184
SUMMARY OF PARTS USED................................................................................................................................................... 185
10.2.1
10.3
12
Jabiru 2200 & 3300 Aircraft Engines
APPENDIX B – OTHER DOCUMENTATION ....................................................................................................................... 184
10.1
10.2
11
Jabiru Aircraft Pty Ltd
Maximum Time In Service ......................................................................................................................................................... 193
Dowel Pins ................................................................................................................................................................................ 193
APPENDIX E – HISTORY OF UPDATES .............................................................................................................................. 198
13.1
13.2
ENGINE SERIAL NUMBER DECODE.......................................................................................................................................... 198
UPDATE HISTORY TABLE ...................................................................................................................................................... 198
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Engine Overhaul Manual
JEM0001-8
1.1
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Table of Figures
Figure 1 – 2200 Engine ................................................................................................................................................... 16
Figure 2 – 3300 Engine ................................................................................................................................................... 16
Figure 3 – Cylinder Numbering Convention .................................................................................................................... 17
Figure 4 – Sealants, Compounds & Lubricants #1 ......................................................................................................... 25
Figure 5 – Sealants, Compounds & Lubricants #2 ......................................................................................................... 25
Figure 6 – Sealants, Compounds & Lubricants #4 ......................................................................................................... 26
Figure 7 – Sealants, Compounds & Lubricants #4 ......................................................................................................... 26
Figure 8 – Sealants, Compounds & Lubricants #3 ......................................................................................................... 27
Figure 9 – Safety Wire / Wire Pliers ................................................................................................................................ 28
Figure 10 – Valve Compressor / Lifter Bleed Tools ........................................................................................................ 28
Figure 11 – Dimensional Details For Lifter Tool.............................................................................................................. 28
Figure 12 – Valve Leakage Vacuum Tester.................................................................................................................... 29
Figure 13 – Valve Spring Compressor / Collet Remover ................................................................................................ 29
Figure 14 – Solid Valve Lifter – Rocker Adjustment Tool ............................................................................................... 29
Figure 15 – Valve Guide Size Gauges ............................................................................................................................ 29
Figure 16 – Leak Down Tester ........................................................................................................................................ 30
Figure 17 – Hand Press & Inserts ................................................................................................................................... 30
Figure 18 – Piston & Ring Installer ................................................................................................................................. 30
Figure 19 – Cylinder Hone Helper .................................................................................................................................. 30
Figure 20 – Piston Circlip Remover and Installer ............................................................................................................ 31
Figure 21 – Standard Circlip Pliers ................................................................................................................................. 31
Figure 22 – Optical Tachometer...................................................................................................................................... 31
Figure 23 – Crankshaft / Flywheel Drilling Jig (for Dowels) ............................................................................................ 31
Figure 24 – Degree Wheel .............................................................................................................................................. 32
Figure 25 – Supplementary Oil Pressure Gauge ............................................................................................................ 32
Figure 26 – Crankshaft Run-Out Test Bed ..................................................................................................................... 32
Figure 27 – Ignition Coil Tester ....................................................................................................................................... 32
Figure 28 – “Finger Bar” .................................................................................................................................................. 33
Figure 29 – Cam Timing Tool (Hydraulic Lifter) .............................................................................................................. 33
Figure 30 – Carburettor Needle Seat Remover and Installer ......................................................................................... 33
Figure 31 – “Crowsfoot” Adaptors ................................................................................................................................... 34
Figure 32 – Crankcase Dry Fit Through-Bolts and Nuts ................................................................................................. 34
Figure 33 – Dial gauge used to locate TDC .................................................................................................................... 34
Figure 34 – Crankcase Stud Remover ............................................................................................................................ 34
Figure 35 – Crankcase Dowel Remover ......................................................................................................................... 35
Figure 36 – Crankshaft Welch Plug Installer / Remover ................................................................................................. 35
Figure 37 – Universal Joint tool FU14B .......................................................................................................................... 35
Figure 38 – Torque Wrench & Crowsfoot Adaptor Setting 1 .......................................................................................... 36
Figure 39 – Torque Wrench & Crowsfoot Adaptor Setting 2 .......................................................................................... 36
Figure 40 – Using A Crowsfoot Adaptor ......................................................................................................................... 37
Figure 41 – Safety Wire Details ...................................................................................................................................... 39
Figure 42 – Safety Wire Installation Using a Twister/Pliers & By Hand .......................................................................... 39
Figure 43 – Engine Stand ............................................................................................................................................... 40
Figure 44 – Measuring Propeller Flange & Crank Run-Out ............................................................................................ 41
Figure 45 – Cylinder Head Disassembly ......................................................................................................................... 42
Figure 46 – Removing Flywheel Cap Screws & Distributor Drive Housings................................................................... 43
Figure 47 – Removing Flywheel...................................................................................................................................... 44
Figure 48 – Remove Timing Gearbox Case ................................................................................................................... 44
Figure 49 – Hidden Sump Screws .................................................................................................................................. 45
Figure 50 – Starter Motor Disassembly .......................................................................................................................... 45
Figure 51 – Removing Crankshaft Timing Gear & Dowels ............................................................................................. 46
Figure 52 – Remove Cylinders........................................................................................................................................ 46
Figure 53 – Remove Pistons ........................................................................................................................................... 47
Figure 54 – Front Seal & Oil Pump Removal .................................................................................................................. 47
Figure 55 – Oil Return Manifolds .................................................................................................................................... 48
Figure 56 – Crankcase & Locking Plate .......................................................................................................................... 48
Figure 57 – Split Crankcase ............................................................................................................................................ 49
Figure 58 – Remove Oil Strainer..................................................................................................................................... 50
Figure 59 – Remove Con-Rods ...................................................................................................................................... 50
Figure 60 – Welch Plug & Propeller Flange Removal From Crankshaft ........................................................................ 51
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Jabiru 2200 & 3300 Aircraft Engines
Figure 61 – Stud & Broken Cap Screw Removal ............................................................................................................ 58
Figure 62 – Crankshaft End Detail (Dowel Holes) .......................................................................................................... 59
Figure 63 – Starfish Flywheel.......................................................................................................................................... 60
Figure 64 – Crankshaft Measurement ............................................................................................................................ 61
Figure 65 – Radius Crank Centre Holes ......................................................................................................................... 61
Figure 66 – Steel Con-Rod ............................................................................................................................................. 61
Figure 67 – Rear Cam Journal Oil Feed ......................................................................................................................... 63
Figure 68 – Fuel Pump Oil Drain..................................................................................................................................... 63
Figure 69 – Crankcase Fretting....................................................................................................................................... 64
Figure 70 – Measuring Crankcase Bearing Tunnel ........................................................................................................ 64
Figure 71 – Removing Studs and Dowels from Crankcase ............................................................................................ 65
Figure 72 – Main Bearings .............................................................................................................................................. 66
Figure 73 – Hydraulic Lifter (top left), Solid Lifter (lower left), Roller Follower (right) ..................................................... 67
Figure 74 – Hydraulic Lifter Inspection ........................................................................................................................... 67
Figure 75 – 2-Ring Camshaft .......................................................................................................................................... 68
Figure 76 – Roller Cam Lobe .......................................................................................................................................... 68
Figure 77 – Port Plate Evolution ..................................................................................................................................... 69
Figure 78 – Modified Port Details .................................................................................................................................... 69
Figure 79 – Inspecting Oil Pump ..................................................................................................................................... 70
Figure 80 – Oil Pressure Relief Valve ............................................................................................................................. 70
Figure 81 – Measuring Cylinder Length .......................................................................................................................... 72
Figure 82 – Measuring Cylinders & Pistons .................................................................................................................... 73
Figure 83 – Cylinder hone Pattern .................................................................................................................................. 74
Figure 84 – Cracking Between Valves, Recessed Cylinder Spigot ................................................................................ 75
Figure 85 – Valve Measuring .......................................................................................................................................... 75
Figure 86 – Valve Damage ............................................................................................................................................. 76
Figure 87 – Valve Guides ................................................................................................................................................ 77
Figure 88 – Measure Guide Wear (Telescopic Gauge Left & Middle, Go-No-Go Gauge Right) .................................... 77
Figure 89 – Valve Seat Geometry ................................................................................................................................... 79
Figure 90 – Recessed Valve Seat, Valve Being Cut ...................................................................................................... 79
Figure 91 – Vacuum Test Rig ......................................................................................................................................... 80
Figure 92 – Valves Assembly, Cylinder Head / Cylinder Lapping .................................................................................. 81
Figure 93 – Valve Springs, Pushrods ............................................................................................................................. 82
Figure 94 – Valve Spring Washer Thickness .................................................................................................................. 82
Figure 95 – Pushrod Tube End ....................................................................................................................................... 82
Figure 96 – Fitting Rocker Bush...................................................................................................................................... 83
Figure 97 – Solid VS Hollow Valve Rockers ................................................................................................................... 84
Figure 98 – 2200 Engine Sumps .................................................................................................................................... 84
Figure 99 – 3300 Engine Sumps .................................................................................................................................... 85
Figure 100 – Different Ignition Coil Models (Honda on Left, Jabiru on Right). ............................................................... 87
Figure 101 – Damaged Flywheel “Starfish” .................................................................................................................... 88
Figure 102 – Starter Motor Old & New ............................................................................................................................ 89
Figure 103 – Typical Disassembled Starter Motor .......................................................................................................... 89
Figure 104 – Starter Motor Overhauling ......................................................................................................................... 90
Figure 105 – Checking Engine Mount Plate Trueness ................................................................................................... 90
Figure 106 – Distributor Gears & Case ........................................................................................................................... 91
Figure 107 – Adjusting High Tension Lead Caps ........................................................................................................... 92
Figure 108 – Carburettor Updates .................................................................................................................................. 94
Figure 109 – Carburettor Schematic ............................................................................................................................... 94
Figure 110 – Disassembling Carburettor #1 ................................................................................................................... 95
Figure 111 – Disassembling Carburettor #2 ................................................................................................................... 95
Figure 112 – Fitting New Float Needle Seat ................................................................................................................... 96
Figure 113 – Carburettor Jets & Diaphragm ................................................................................................................... 96
Figure 114 – Fuel Pumps (Type 1 on Left, Type 2 on Right) .......................................................................................... 97
Figure 115 – Crankshaft Painting, Degree Wheel ........................................................................................................ 100
Figure 116 – Blueing Bearings, Assembling Rods........................................................................................................ 101
Figure 117 – Measuring Connecting Rods ................................................................................................................... 101
Figure 118 – Fit Connecting Rods ................................................................................................................................ 102
Figure 119 – Crankcase Assembly Preparation ........................................................................................................... 104
Figure 120 – Crankcase Dowels ................................................................................................................................... 104
Figure 121 – Crankcase Clamping Preparation ............................................................................................................ 105
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Jabiru 2200 & 3300 Aircraft Engines
Figure 122 – Fitting Thrust Bearings ............................................................................................................................. 105
Figure 123 – Fitting Oil Pickup Tube ............................................................................................................................. 106
Figure 124 – Checking Crankshaft End Float, Installing Solid Lifters ........................................................................... 106
Figure 125 – Cam Timing Gear Assembly .................................................................................................................... 107
Figure 126 – Assembling Cam & Fitting to Crankcase ................................................................................................. 107
Figure 127 – Thrust Direction Markings For Pistons .................................................................................................... 108
Figure 128 – Installation of Pistons With Valve Relief .................................................................................................. 108
Figure 129 – Fitting Circlip to Piston ............................................................................................................................. 109
Figure 130 – Fitting Wire-Type Piston Circlips .............................................................................................................. 109
Figure 131 – The Two Sides of Circlips ........................................................................................................................ 110
Figure 132 – Clip Installation Detail .............................................................................................................................. 110
Figure 133 – Over-Compressed and New Clips ........................................................................................................... 111
Figure 134 – Checking Piston Ring Gap ....................................................................................................................... 111
Figure 135 – Compression Ring Cross Section ............................................................................................................ 112
Figure 136 – Piston / Ring / Cylinder Assembly............................................................................................................ 113
Figure 137 – Through Bolt Nut Installation Detail ......................................................................................................... 114
Figure 138 – 12-Point Nuts, 7/16” Hardware (on right) ................................................................................................. 114
Figure 139 – Cylinder Head Comparison (2200 head on left, 3300 on right). .............................................................. 115
Figure 140 – Fitting Valves to Head, Fitting Bushes to Rockers .................................................................................. 116
Figure 141 – Cylinder Head Welch Plug & Lube Tube Installation. .............................................................................. 116
Figure 142 – Ignition Coil Insulating Washer, Alternator Stator Thickness .................................................................. 118
Figure 143 – Flywheel Assembly .................................................................................................................................. 119
Figure 144 – Installation of Oil Feed Tubes & Tacho Pickup Post ............................................................................... 120
Figure 145 – Hall affect Tacho Sender ......................................................................................................................... 120
Figure 146 – Installation of Seals & Assembly.............................................................................................................. 121
Figure 147 – New Distributor Shaft Bush Fitted – nopic x 1 ......................................................................................... 121
Figure 148 – Assembling Distributor Gear to shaft ....................................................................................................... 122
Figure 149 – Applying Sealant to Case, Fitting to Crank .............................................................................................. 125
Figure 150 – Fitting The Second Case Half .................................................................................................................. 125
Figure 151 – Tightening The Front Crankcase Studs ................................................................................................... 126
Figure 152 – Applying Sealant and O-Ring to Cylinder Base ....................................................................................... 126
Figure 153 – Fitting Gudgeon Pin ................................................................................................................................. 127
Figure 154 – Fitting Cylinder, Inserting & Tightening Through-Bolts ............................................................................ 127
Figure 155 – Piston Orientation .................................................................................................................................... 127
Figure 156 – Torque Seal Applied ................................................................................................................................ 128
Figure 157 – Universal Joint tool FU14B (FU16B for ½” Socket) ................................................................................. 129
Figure 158 – Measuring Top Dead Centre ................................................................................................................... 130
Figure 159 – Setting Cam Timing ................................................................................................................................. 131
Figure 160 – Checking Cam Timing #1 ........................................................................................................................ 131
Figure 161 – Checking Cam Timing #2 ........................................................................................................................ 132
Figure 162 – Fitting Sump ............................................................................................................................................. 133
Figure 163 – Oil Filler Tube Installation ........................................................................................................................ 133
Figure 164 – Sealing Engine Mount Plate .................................................................................................................... 134
Figure 165 – Fitting Engine Mount Plate ....................................................................................................................... 134
Figure 166 – Engine Mount Plate Screw Locations ...................................................................................................... 135
Figure 167 – Fitting Distributor Case & Setting Timing ................................................................................................. 136
Figure 168 – Setting Distributors, Checking Rotor Position .......................................................................................... 136
Figure 169 – Checking Rotors, Tightening Distributor Case ........................................................................................ 137
Figure 170 – Gearbox Installation ................................................................................................................................. 137
Figure 171 – Applying Loctite, Fitting Dowels. .............................................................................................................. 138
Figure 172 – Flywheel & Crank Timing Marks .............................................................................................................. 139
Figure 173 – Fitting & Tightening Flywheel Cap Screws .............................................................................................. 139
Figure 174 – Ignition Post & Alternator Stator Installation ............................................................................................ 140
Figure 175 – Distributor Cap Installation ....................................................................................................................... 141
Figure 176 – Fitting Hydraulic Lifter To Crankcase....................................................................................................... 143
Figure 177 – Crankcase & Locking Plate ...................................................................................................................... 143
Figure 178 – Oil Return Manifold Fitted ........................................................................................................................ 143
Figure 179 – Applying Thread Lubricant & Tightening Lower Head Screw .................................................................. 144
Figure 180 – Fitting Rockers #1 .................................................................................................................................... 144
Figure 181 – Fitting Rockers #2 .................................................................................................................................... 144
Figure 182 – Fitting Rockers #3 .................................................................................................................................... 145
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Jabiru 2200 & 3300 Aircraft Engines
Figure 183 – Rocker Lube (Left) & Crankcase Oil Port Blanking Plug ......................................................................... 145
Figure 184 – Valve Clearance Adjustment (Solid Lifter) ............................................................................................... 146
Figure 185 – Induction Manifold Installation ................................................................................................................. 146
Figure 186 – Fitting Induction Pipes to Plenum Chamber ............................................................................................ 147
Figure 187 – Fitting Carburettor .................................................................................................................................... 147
Figure 188 – Exhaust Installation .................................................................................................................................. 148
Figure 189 – Firing Order of Distributor Caps ............................................................................................................... 148
Figure 190 – HT Leads Fitted To Engine ...................................................................................................................... 149
Figure 191 – Fitting Seal To Housing ........................................................................................................................... 149
Figure 192 – Front Seal Housing Ready To Fit ............................................................................................................ 150
Figure 193 – Preparing To Fit Propeller Flange ............................................................................................................ 150
Figure 194 - Installing the Propeller flange ................................................................................................................... 152
Figure 195 – Fitting Oil Pump & Port Plate ................................................................................................................... 152
Figure 196 – Engine Turning Tool, Installed Oil Pump ................................................................................................. 153
Figure 197 – Lapping Oil Pressure Relief Valve ........................................................................................................... 153
Figure 198 – Oil Pressure Relief Valve Assembly ........................................................................................................ 154
Figure 199 – Engine Ground Running Rig .................................................................................................................... 156
Figure 200 – Oil Pump Details ...................................................................................................................................... 164
Figure 201 – Magnet Tests ........................................................................................................................................... 165
Figure 202 – Crankcase Fretting................................................................................................................................... 191
Figure 203 – Stripping Crankcases ............................................................................................................................... 192
Figure 204 – De-Burring Crankcase After Surfacing & Line Boring.............................................................................. 192
Figure 205 – Drilling Fixture – Crankshaft Side on Left, Flywheel Side On Right ....................................................... 193
Figure 206 – 15/64” Drill (Left), 6mm Ream (Centre), UNF Cap Screws (Right) ......................................................... 194
Figure 207 – Guide positioned on crankshaft. .............................................................................................................. 194
Figure 208 – Drilling & Reaming Crankshaft – ILLUSTRATION ONLY. ....................................................................... 195
Figure 209 – Aligning Guide & Fitting To Flywheel. ...................................................................................................... 195
Figure 210 – Drilling & Reaming Flywheel – ILLUSTRATION ONLY. .......................................................................... 196
Figure 211 – Flywheel to crankshaft assembly drawing ............................................................................................... 197
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JEM0001-8
1.2
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Table of Tables
Table 1 – List of Approved Revisions ............................................................................................................................. 12
Table 2 – The Spanner Scale ......................................................................................................................................... 14
Table 3 – Mandatory Replacement Items – Full Overhaul ............................................................................................. 53
Table 4 – Mandatory Replacement Items – Top End Overhaul ...................................................................................... 54
Table 5 – Carburettor Tuning .......................................................................................................................................... 93
Table 6 – Hardware Configuration Summary................................................................................................................ 128
Table 7 – Oil Recommendations for Run-In. ................................................................................................................. 155
Table 8 - Troubleshooting ............................................................................................................................................. 158
Table 9 – Torque Specifications.................................................................................................................................... 160
Table 10 – Build Tolerances ......................................................................................................................................... 161
Table 11 – Mandatory Replacement Items – Multi-Cycle Parts .................................................................................... 162
Table 12 – Clearance and Wear Limits ......................................................................................................................... 163
Table 13 – Electrical System Specifications ................................................................................................................. 164
Table 14 – Engine Disassembly.................................................................................................................................... 166
Table 15 – Build Sheet A (EXAMPLE) .......................................................................................................................... 167
Table 16 – Build Sheet A .............................................................................................................................................. 168
Table 17 – Build Sheet B .............................................................................................................................................. 169
Table 18 – Build Sheet C .............................................................................................................................................. 170
Table 19 – Build Sheet D .............................................................................................................................................. 171
Table 20 – Build Sheet E .............................................................................................................................................. 171
Table 21 – Build Sheet F ............................................................................................................................................... 172
Table 22 – Build Sheet G .............................................................................................................................................. 173
Table 23 – Build Sheet H .............................................................................................................................................. 174
Table 24 – Ground Run-In Procedure ........................................................................................................................... 175
Table 25 – Sheet J – Post Run Inspection .................................................................................................................... 176
Table 26 – Measure & Clearance Record Sheet .......................................................................................................... 177
Table 27 – Top End Build Sheet A ................................................................................................................................ 178
Table 28 – Top End Build Sheet C ............................................................................................................................... 179
Table 29 - Top End Build Sheet E ................................................................................................................................ 179
Table 30 – Top End Build Sheet F ................................................................................................................................ 180
Table 31 – Top End Build Sheet G ............................................................................................................................... 181
Table 32 – Top End Build Sheet H ............................................................................................................................... 182
Table 33 – Top End Measure & Clearance Record Sheet ........................................................................................... 183
Table 34 – Job Traveller ............................................................................................................................................... 184
Table 35 – Summary of Parts Used .............................................................................................................................. 185
Table 36 – Bulk Strip Checklist ..................................................................................................................................... 186
Table 37 – Job Summary Sheet.................................................................................................................................... 187
Table 38 – Wear Factors............................................................................................................................................... 188
Table 39 – Mandatory Updates ..................................................................................................................................... 189
Table 40 – Update History ............................................................................................................................................ 198
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Engine Overhaul Manual
Jabiru Aircraft Pty Ltd
JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
2 General Information
WARNING:
Jabiru Aircraft Pty Ltd has devoted significant resources and testing to develop the Jabiru aircraft
engines. These engines are intended to be installed in accordance with the details given in the
appropriate Jabiru Engine Installation Manual. Any other uses or applications may be extremely
hazardous, leading to property damage, or injury or death of persons on or in the vicinity of the
vehicle. Jabiru Aircraft Pty Ltd does not support the use of this engine in any applications which do
not meet the requirements of the appropriate Jabiru Engine Installation Manual. Any non-compliant
installation may render the aircraft un-airworthy and will void any warranty issued by Jabiru.
The Jabiru Aircraft Engines are designed to be operated and maintained only in strict accordance
with the appropriate Instruction and Maintenance Manual. Any variation of any kind, including
alteration to any component at all, whether replacement, relocation, modification or otherwise
which is not strictly in accordance with these manuals may lead to dramatic changes in the
performance of the engine and may cause unexpected engine stoppage, engine damage or harm to
other parts of the aircraft to which it may be fitted and may lead to injury or death. Jabiru Aircraft
Pty Ltd does not support any modifications to an engine, its parts, or components. Any such
actions may render the aircraft un-airworthy and will void any warranty issued by Jabiru.
Maintenance and modification cannot be supervised by the manufacturer. Maintenance requires
extreme cleanliness, exact parts, precise workmanship and proper consumables. It is your
responsibility to ensure absolute attention to detail no matter who may become involved in work on
this engine. Your safety, your life and your passenger’s lives rely on precise and accurate following
of instructions in this manual.
In exchange for the engine manual provided by Jabiru Aircraft Pty. Ltd. (“Jabiru”) I hereby agree to
waive, release, and hold Jabiru harmless from any injury, loss, damage, or mishap that I, my
spouse, heirs, or next of kin may suffer as a result of my use of any Jabiru product, except to the
extent due to gross negligence or willful misconduct by Jabiru. I understand that proper skills and
training are essential to minimize the unavoidable risks of property damage, serious bodily injury
and death that arise from the use of Jabiru products.
2.1



List of Effective Pages / Issue Status
This manual is revised as a whole. All pages retain the revision status of the overall document.
Altered text is shown in red.
In cases where the data contained in Appendix A is altered and the information in the main body of the
manual is not an additional issue suffix will be applied: Issue 4-A1 indicates Issue 4 of the manual and
Revision 1 of Appendix A. Whenever the main manual is updated this suffix is re-set
Table 1 – List of Approved Revisions
Issue
1
2
3
4
Reason for Issue
Initial Issue
Added notes re crankcase dowel fit, general update
2: Reading this manual section added. 3.6: Tool & gauge notes expanded. 4: Inspect before cleaning,
7/16” bolt details, oil return manifolds. 5.8: engine cooling notes added. 5.9: notes re flywheel screws.
5.10: oil return manifold notes. 5.11: barrel length notes, valve vacuum unit correction, pushrod length
notes, hollow pushrod & rocker details. 5.15.2: new notes re fuel pump. 7.3: circlip notes, alternator
installation notes.
Alter header. Add safety wire, hardware notes. Alter build book format. Create standard tables of
torques, dimensions and clearances. Roller follower references added. Loctite 518 references added.
Top valve spring washer inspection notes added. Rocker arm length note added. Flywheel dowel fit
notes added. Reciprocating part weight limits added. 12-point 7/16” nuts added. Valve seat details
altered.
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Issue
5
7
8
2.2
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

2.3

2.4
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

Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Reason for Issue
Appendix A Tables Altered. Parts table updated. Table 13: spark plug gap removed. Pushrod cover
circlip installation details added (Section 7.3.4 & Figure 182). Add certification basis notes (Section
2.4). Con rod installation altered (Section 7.1.3). Allowable compression side ring clearance altered
(Table 12). Through bolt installation detail updated (Section 7.8, 7.3.3). Add details for series-wound
alternator (Table 13). Update propeller flange installation details (Section 7.8.16 and 5.9.1.3). Add
details for pistons with valve relief (Section 7.3.1, 7.8)
Ground run-in procedure checklist updated (Section 9.9.10)
Corrections made to Mandatory check and Mandatory replacement items (Section 5.2)
Corrections made to Mandatory Replacement Parts table (Appendix D)
Firing order of distributor caps changed to be looking from flywheel end (Figure 189)
Correction of upper limit main bearing clearance Table 12
Correction of build order for crankcase camshaft assembly 9.9.3 B Build Sheet
Correction – Torque flywheel bolts in one step to value specified in Table 9
Corrections made to Mandatory replacement items Top End Overhaul (Section 5.3)
Corrections made to Mandatory replacement items Full Overhaul (Section 5.2)
Spark plug torque setting corrected (section 9.1)
Corrections made to overhaul tools and equipment (Section 3.7)
Change Oil pressure limits for Hydraulic Lifter engines (220-350 kPa)
Add note to prime and install hydraulic lifters with side bleed hole facing up
Correct Distributor firing order diagram (Figure 189)
Change alternator stator screw thread locker to Loctite 263 (section 7.5.2)
Change to Subassembly E Build Sheet – Flywheel, Ignition Coils, Starter Motor And Alternator
Correct new build clearance tolerances (section 9.5)
Add notes to Flywheel attachment procedure (section 7.8.7)
Add note to Propeller Flange installation procedure (section 7.8.16)
Reference to JEM0001 made in build sheets
Update engine photographs (Figure 1 and Figure 2)
Add alternator electrical load limit to section 9.6
Add note to check the valve rotates correctly on a set of collets (section 7.3.4)
Introduction
This Engine Overhaul Manual has been written to cover the 4-cylinder 2200 and 6-cylinder 3300 Jabiru
engines. Many engine components are common to both engines, for example the cylinders, pistons,
connecting rods etc, as well as many accessories and consequentially the procedures in this Manual
apply equally to both engines.
Before attempting an overhaul the technician must be fully conversant with the appropriate Engine
Instruction & Maintenance Manual and any relevant Service Bulletins, Service Letters or other
manufacturer’s data. Current information is available from the Jabiru Aircraft (Australia) web site –
www.jabiru.net.au .
Overhauls must only be carried out by an approved person. Depending on the country and the
category of the aircraft this may be a Licensed Aircraft Maintenance Engineer, an RA-Aus Level 2 or
equivalent. The responsibility for determining what qualifications are necessary to carry out an overhaul
belongs to the person carrying out the work.
Applicability
This manual is applicable to all 2200 and 3300 engine models and variants.
Certification Basis
The 2200C engine is type Certified to the CS-22 Subpart H standard. Various 2200 and 3300 engine
models also comply with the requirements of ASTM F2339.
These standards are not equivalent to FAR 33 or CS-E: CS-22 Subpart H and ASTM F2339 are
simplified engine design standards designed to be suitable for small aircraft with up to two seats
certified using CS-22, CS-VLA or similar design standards.
In all cases, participants in these categories accept that the aircraft, engines and propellers are not
manufactured to the same standards as aircraft in normal categories and that different reliability
expectations apply.
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2.5
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


2.6

Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Reading This Manual
If you are reading this manual on a computer and want to be able to quickly zoom in and out: Hold
down the Ctrl key while rotating the wheel button on your mouse. In most programs this will instantly
zoom in or out.
To do the same thing on a modern laptop either plug in a wheel mouse as detailed above or use the
built-in track-pad. Put two fingers on the pad close together then move then apart diagonally. To
reverse, put two fingers on the pad at opposite diagonal points on the pad and bring them together
diagonally. This works on most modern PC-laptops.
This document has been created with hyperlinks between referenced items. So, when reading the
manual on a computer you can click on the page number of an item on the table of contents and the
computer will skip to that page. Also, if a paragraph says “refer to Section 5.9” – then you can click on
the “5.9” and automatically skip to that page. Similarly, if Figures or Tables are referenced.
To open a search window press “Ctrl-f”. Depending on the program, this will normally open a small
search window where you can enter keywords. For example, searching for the word “life” will allow you
to quickly find all reference to lifed maintenance items.
Degree of Difficulty
In this manual we have used a “spanner scale” to help overhaulers approach a job. Anyone
considering undertaking a task in this manual must realistically assess themselves against this scale
and not attempt any task for which they lack knowledge or the required tools.
Table 2 – The Spanner Scale
The Spanner Scale
Translation
Simple, basic, straightforward. A careful layman, with guidance, can
achieve this.
Straightforward, but with some technical bits. Basic knowledge, care
and guidance needed.
Straightforward, but requires special tools, training and/or judgement.
Sound basic knowledge guidance and a careful approach are required.
A technical job. Take your time, double-check everything. Only for the
experienced overhauler.
A difficult job. Requires special tools, solid skills, good judgement.
Only for experts.
2.7


2.8




Manual layout
This Manual suggests that an engine overhaul will be conducted in three stages: Disassembly,
Inspection and assessment, and Assembly. The intention is that an engine will initially be stripped and
the mandatory replacement parts will be discarded. The remaining parts will be inspected and assessed
for return to service and a single parts order will then be placed.
Final assembly can take place once all the required parts are present.
Engine life
Engine life is expressed here in cycles, with 1 cycle being nominally in the vicinity of 1,000 hours, the
actual number of hours achieved being heavily dependant on the use of correct operating and
maintenance procedures and, to a lesser degree, operating conditions.
The expected life (expressed as time between complete overhauls) of a correctly operated and
maintained Jabiru engine is 2 cycles, with a top end overhaul taking place at 1 cycle.
Various components of the engine have a service life which is determined “on condition” – that is the
overhauler must examine the part and make a judgement as to the part’s suitability for re-use. Other
parts are evaluated both on condition and by a fixed maximum life – for example valves which are
replaced around 1,000 hours (See Sections 5.1, 5.2 and 5.3).
Engine life is measured via direct tachometer hour meters or “Hobbs” meters. Air switches or scaled
hour readings based on cumulative power output are not to be used to determine when overhauls or
services are due.
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2.9


Jabiru 2200 & 3300 Aircraft Engines
Complete overhaul, top end overhaul, wear tolerances
While the overall thrust of this Manual is complete overhaul, distinction must be made between a
complete overhaul and top end overhaul: the objective of a complete overhaul is to return the engine to
a condition where it can be reasonably expected to achieve 2 cycles, while the objective of a top end
overhaul is to return the top end of the engine (i.e. big ends, cylinders, pistons and cylinder heads) to a
condition where it can be reasonably expected to achieve 1 cycle to take the engine to the next
complete overhaul.
Consequentially the allowable wear tolerances for a top end overhaul, which is intended to achieve 1
cycle, will be different to the allowable wear tolerances for a complete overhaul, which is intended to
achieve 2 cycles.
2.10 Mandatory updates




Jabiru has been producing engines for many years, and over that time we have made some
improvements to our engine designs in light of operating experience. As a result we have compiled a list
of mandatory updates that must be made to older engines during overhaul.
During the Inspection and assessment stage these modifications will be addressed for each
Subassembly.
The requirements of these modifications must be taken into account when ordering parts.
Section 10 refers.
2.11 Mandatory replacement of parts

During overhaul (either complete or top end) some parts must be replaced regardless of condition: for
example all bolts, all seals, O-rings, etc. Detailed listings will be found in the Inspection and assessment
stage.
2.12 Recording


Careful records of all overhauling work must be completed. It is strongly recommended that the
overhauler print out the build sheets given as a part of this manual and use them to record all the details
of the job.
The overhaul booklets included in Section 9 are to be used for a top end overhaul – using only those
pages relevant to the parts of the engine being renewed.
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Jabiru 2200 & 3300 Aircraft Engines
2.13 General Description

The engines covered in this manual are all direct drive four and six cylinder, horizontally opposed, aircooled models.
Figure 1 – 2200 Engine
Figure 2 – 3300 Engine
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Jabiru 2200 & 3300 Aircraft Engines
2.13.1 Engine identification
 Engine serial numbers are located on the engine number plate that is affixed to the right rear top of the
crankcase. An explanation of the cross-reference of engine numbers may be found in Section 13.1.
2.13.2 Build Configurations



At many places in this manual a serial number range will be referenced with respect to an aspect of the
engine build – i.e. S/No. 200 – 250 use a triple-flexed widget while engines outside that range have
double-flexed widgets.
In all cases this information refers to the configuration of the engine when it was originally built.
In many cases this information will be changed – such as if the engine is upgraded to a newer
configuration at overhaul. The overhauler must be aware of the potential for these changes and confirm
the engine configuration before beginning re-assembly.
2.13.3 Part Identification
 Several components of the engines have been revised since the engines entered production. In some
cases important differences between parts cannot be distinguished easily by inspection. In these cases
identification markings have been applied to the parts. Where applicable, these markings will be shown
and explained in the body of the manual below.
2.13.4 Cylinder Numbering Convention
Figure 3 – Cylinder Numbering Convention
2.13.5 Cylinder heads
 The cylinder heads are machined from solid aluminium billet and are fitted to the cylinders by means of
6 retaining cap screws per head.
2.13.6 Valves, valve guides and seats
 Stainless steel valves run in press fitted aluminium/bronze valve guides and seat against nickel steel
valve seats that have been shrunk fit into the cylinder heads.
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Jabiru 2200 & 3300 Aircraft Engines
2.13.7 Cylinders
 Cylinders are machined in one piece from solid bar 4140 chrome molybdenum alloy steel, with the
pistons running directly in the steel bores.
2.13.8 Pistons
 The pistons are machined from aluminium castings and have 3 rings, the top 2 rings being cast iron to
compliment the chrome molybdenum cylinder bores. The gudgeon pin (wrist pin) is of the full floating
type and is retained by a circlip at each end.
2.13.9 Connecting rods
 The connecting rods are machined from solid bar 4140 chrome molybdenum alloy steel.
They have replaceable bearing inserts in the crankshaft ends (big ends) and the piston ends (small
ends) are machined to fit the gudgeon pin. The big end bearing end caps are fixed to the connecting
rod by two Allen head cap screws through the rod into the end cap.
2.13.10
Crankshaft
 The crankshaft is machined from solid bar 4140 chrome molybdenum alloy steel and is stress relieved
using a heat treatment process. The journals are precision ground prior to being inspected by the MPI
(Magnetic Particle Inspection) method.
2.13.11
Crankcase
 The crankcase is machined from solid aluminium billet and consists of two halves divided along the
vertical centreline and fastened together by the studs and nuts that retain the cylinders. The mating
surfaces of the crankcase halves are joined without the use of a gasket, and the main bearing bores are
machined for the use of automotive slipper type bearings. Thrust bearings are located fore and aft of
the front double main bearing. The crankcase forms the bearings for the camshaft.
2.13.12
Camshaft
 The camshaft is machined from solid bar 4140 chrome molybdenum alloy steel and is hardened using a
nitriding process.
2.13.13
Valve operating mechanism
 The camshaft is gear driven from the crankshaft. The camshaft operates cam followers that operate the
valves though pushrods and valve rocker arms. The valve rocker arms are made from steel, induction
hardened and mounted in the cylinder heads on steel shafts through low friction bronze/steel bushes.
2.13.14

Solid lifters
2200 and 3300 engines earlier than serial number [22A-2068] or [33A-961] utilise solid lifters driven by
a 330° camshaft.
2.13.15
Hydraulic lifters
 2200 and 3300 engines from serial number [22A-2068] or [33A-961] use hydraulic lifters.
2.13.16
Roller Followers
 2200 and 3300 engines from serial number [22A-3596] or [33A-2539] use hydraulic lifters with roller
bases.
2.13.17
Lubricating system
 All engines employ a full pressure wet sump lubrication system. A positive-displacement pump driven
from the front of the camshaft provides oil pressure, and oil is circulated to the oil galleries through a
spin-on automotive type oil filter. An adaptor fitted beneath the oil filter feeds oil to the oil cooler.
 The primary lubrication sections of the engine – crankshaft, big ends etc – use this full pressure
lubrication system. Secondary lubrication sections of the engine such as the cylinder heads and
gearbox use low pressure lubrication systems while tertiary lubrication sections such as piston/bore
lubrication uses splash lubrication.
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Jabiru 2200 & 3300 Aircraft Engines
2.13.18
Cooling system
 Cooling is provided by air pressure that is built up above the cylinder heads in the ram air ducts and
discharged, with an accompanying pressure drop, down through the cooling fins on the cylinder heads
and cylinders and out of the lower rear of the engine cowling.
2.13.19

All engines are equipped with a BING brand pressure compensating float type carburettor. The inlet
manifold is mounted in direct contact with the engine oil sump, thus providing a relatively constant
temperature
in
the
manifold
for
more
uniform
vaporisation
of
fuel.
Fuel-air mix is distributed from the manifold to the cylinder heads by individual tubes.
2.13.20

Induction system
Ignition system
Dual transistorised ignition is provided by two flywheel mounted rare earth magnets that energise two
fixed coils mounted adjacent to the flywheel. The resulting high-voltage current is distributed to the
spark plugs by two gear driven distributors and associated high tension leads. The ignition system has
fixed timing and is fully redundant, self-generating, and does not depend on battery power for operation.
Spark is not generated below 275rpm crankshaft speed.
2.13.21
Electrical charging system
 An integral alternator, using rare earth magnets, provides alternating current for battery charging and
powering electrical accessories. The alternator is attached to the flywheel and is driven directly by the
crankshaft. The alternating current goes to a firewall-mounted regulator and thence to the aircraft
electrical system.
2.13.22

Starter motor
The 1.5kw starter motor is mounted to the engine mounting plate at the left rear of the engine with the
drive gear positioned above and ahead of the flywheel when not engaged.
2.13.23
Sump
 The engines are equipped with a wet sump lubrication system. The sump is a cast aluminium item
fitted to the underside of the engine and also provides the mounting points for the induction system and
oil cooler.
2.14 Assessing An Engine

While not intended as a complete guide, the overhauler must be aware that the following factors will
affect the service life of an engine. With familiarity the overhauler will be able to look at an engine on
receipt, assess it and have an excellent idea of what will need to be done and what has caused any
issues. For example:
1. Overheating causes higher than normal oil consumption.
2. Hydraulic engines prior to oil fed rockers (hollow pushrods) have higher wear in rocker bushes.
3. Non adherence to published bulletins will shorten engine life. It is essential that operators keep upto-date with all updated Jabiru Service information.
4. Operation with defective valves (partially sealing valves) will end with structural failures and
expensive repairs.
5. Operation with poor quality or incorrect fuel will cause problems.
6. Oil/fuel additives are not to be used; some have proven to have highly detrimental effects on
engines.
7. Incorrect load (propellers) will shorten engine life.
8. The installation and matching of the engine and propeller to the aircraft are absolutely essential for
getting the best out of Jabiru Engines. Guidance material is available in the Jabiru Engine
Installation Manuals and Instruction & Maintenance Manuals.
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3 General overhaul procedures
3.1






Manual layout
This manual is intended for use by experienced technicians and while all processes will be explained as
clearly as possible, some knowledge is assumed. This manual is not intended to be sufficient reference
for a person with no other training to safely complete an overhaul.
The sections of the Manual are arranged in the stages in which work will be performed: the engine is
stripped, all components are either discarded (mandatory replacement items) or cleaned then inspected
and assessed for return to service and parts are ordered then the engine is assembled and finally
tested and run-in.
This Manual will describe the overhaul procedures by individual Subassembly of the engine, thus
dividing the manual, for all practical purposes, into a series of individual handbooks dealing with each
Subassembly in turn.
The disassembly stage will be described in a slightly different sequence from the Subassemblies used
in the Inspection and assessment and Assembly stages.
Many of the photographs throughout this Manual are of a 2200 engine – the procedures used are
common across Jabiru 4 and 6 cylinder engines, the only difference being the number of cylinders.
Since there are various overhaul practices and instructions of a non-specific nature, such as cleaning
and inspection, which apply equally to all basic engine components, these general instructions will be
grouped together where possible, to avoid repetition.
3.2

Directional References
In all references to orientation such as “the front of the engine” it will be assumed that the engine has
been installed in a tractor configuration and “front” refers to the propeller end of the engine while “rear”
refers to the flywheel end of the engine. “Left hand” and “right hand” refer to the same orientation when
standing behind the engine facing towards the front of the engine.
3.3




Top End Overhaul vs Full Overhaul
While the overall thrust of this Manual is complete overhaul some sections can also be applied to a top
end overhaul.
A top end overhaul means overhauling only the “top end” of the engine: big ends, cylinders, pistons and
cylinder heads. If a top end overhaul is being conducted then only those items listed in Section 5.3
should be removed from the engine during the engine strip procedure.
Note that greater wear tolerances may be used for a top end overhaul than would be used for a
complete overhaul as a top end overhaul is only required to achieve a life of 1 cycle, taking the engine
through to the next complete overhaul, whereas a complete overhaul is intended to return the engine to
a state where it can be expected to achieve a life of 2 cycles.
As for disassembly, on assembly only certain sections of this manual are relevant for a top end
overhaul. These are detailed in Section 6.
3.4


Special Classes of Overhaul
The following section discusses unusual cases, where an engine is presented to the overhauler where
something other than normal operation has taken place.
In general the procedures for dealing with these are the same as those for a normal overhaul, however
the overhauler must be particularly alert and vigilant for unusual features within the engine. For
example, during a severe prop strike the engine mount plate is often bent – sometimes only slightly –
and this sort of damage may be missed if the inspection process is in any way lax.
3.4.1


Bulk Strip
A Bulk Strip is a special class of procedure where an engine is pulled apart, inspected and then put
back together again – generally using all the same components. It is generally called for when
something has happened to put the internal condition of the engine into doubt – such as a propeller
strike, in-flight failure or improper long term storage.
In its purest form a bulk strip will not affect the life of the engine – so an engine which has a bulk strip at
a time in service of 700 hours will still only have 300 hours left to run after the bulk strip has been
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
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
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Jabiru 2200 & 3300 Aircraft Engines
completed and the engine re-assembled. However, often the customer will decide to incorporate a
mini-overhaul or top-end into the bulk strip.
The point of the bulk strip is to check several critical items inside the engine to ensure that it is suitable
to be returned to service. Depending on what has happened to the engine some parts will mandatorily
be replaced.
In addition to the potential damage to the engine which required the bulk strip in the first place it is
Jabiru policy that the engine must be made up-to-date and airworthy before being re-assembled. This
means that items which are listed as a “Mandatory Update” within this manual must be carried out
during a bulk strip as they would be during an overhaul. For example a crankshaft which has no
flywheel dowels must be updated to accept them or replaced by a new assembly during a bulk strip.
3.4.1.1

Jabiru Aircraft Pty Ltd
Bulk Strip Checklist
Personnel carrying out a bulk strip must be qualified to the same degree as those carrying out a full
overhaul.
The tools, equipment, sealants and compounds used in the bulk strip are the same as those used for a
full overhaul – the person carrying out this work must have all available.
Measure crankshaft and propeller flange run-out before disassembling the engine to help gauge the
potential severity of the damage to the engine. Use the procedure detailed in Section 4.4.1.
Engine strip and cleaning are the same as detailed in Section 4.
Check for mandatory updates as detailed in Section 4 and replace / rework parts as necessary.
Re-measure crankshaft and propeller flange run-out on the bench for best accuracy.
MPI test the propeller flange, crankshaft and connecting rods.
Replace all screws used in the propeller flange, flywheel and connecting rod attachments.
Replace O rings and gaskets as required.
Replace piston circlips with new parts
Assembly of the engine is as detailed in Section 7.
Fill out engine build sheets.
Carry out engine test runs
Carry out post-run inspections.
Complete a report for the customer, detailing what was found in the engine and which parts were
replaced.
3.4.2 Propeller strike procedures
 Propeller strike is categorized as being one of 2 types: low power strike and high power strike.
 A low power strike is defined as a propeller strike encountered while the engine is operating at a low
power setting (eg. while taxiing) with a standard Jabiru softwood propeller. Damage to the propeller
must extend no more than 100mm inwards from the blade tips. If any of these parameters are not met
the event is considered to be a high power strike.
 High power strikes also include any other type of abrupt engine stoppage at any other engine operating
condition.
 The flywheel retaining cap screws (6) and propeller flange retaining screws (6) need to be replaced
after any prop strike.
3.4.2.1



Low Power Prop Strike Checklist
The flywheel retaining cap screws (6) and propeller flange retaining screws (6) need to be replaced
after any prop strike.
If a low power strike has been encountered then crankshaft runout must be checked as detailed in
Section 4.4.1 and if necessary the propeller flange and/or the crankshaft may need to be replaced.
When replacing the flywheel and propeller flange cap screws remember that they are held in place with
Loctite 620, which is very strong. They will be very difficult to undo and great care must be taken not to
break any of them. Lock the crankshaft from turning and then apply heat to the area around the cap
screws, and then try to crack each cap screw loose using an Allen key and a 3/8” breaker bar. This step
may involve heating the end of the crankshaft several times until you can safely undo each cap screw.
Details on removing these screws are included in Section 4.5.4. The procedure to be used for replacing
the screws in the propeller flange is the same.
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Jabiru 2200 & 3300 Aircraft Engines
Do NOT apply heat directly to the cap screws because this could weaken the screw material, but rather
apply the heat to the area around the cap screws. This is particularly important because you will need to
apply considerable turning force to undo each cap screw.
Clean out all threads and then prime the threads and the new cap screws with Loctite 7471 cure
accelerator and allow to dry. Apply a few drops of Loctite 620 Retainer to each thread and each cap
screw and tighten in sequence to the recommended torque value from the table of limits. Section 7.8
details the assembly of the flywheel and propeller flange to the engine – these procedures are also to
be used here.
3.4.2.2

Jabiru Aircraft Pty Ltd
High Power Strike Repair Checklist
Jabiru policy for a high power strike is to Bulk Strip in accordance with Section 3.4.1.1: Disassemble,
clean and inspect the engine updated. Re-assemble the engine, complete build sheets, test run, carry
out a post-run inspection and complete a report for the customer.
In particular, carefully check that the engine mount plate has not been bent, check the propeller flange
for condition and straightness and inspect the flywheel connection for damage. Replace the crankshaft
and MPI inspect the connecting rods. Check and carry out any mandatory updates.
3.4.3 Abrupt Engine Stoppage
 An abrupt engine stoppage may be caused by a number of different failures within the engine but
essentially any hard, harsh stoppage of the engine is considered to fall into this category. A piston
failure is a typical example.
 Abrupt engine stoppages are treated the same as high power propeller strike.
3.5
Sequence of Events
1.
2.
3.
4.
5.
6.
Engine Build Sheet / Checklists – fill out the necessary documents to record the details of the
engine. Prepare the necessary sheets to record the configuration / condition of the engine as it
is disassembled, cleaned and inspected.
Disassemble – disassemble the engine to the extent necessary for the proposed work – i.e. the
top end only for a top end overhaul or completely for a full overhaul.
Clean, Inspect, Measure And Assess – clean the engine components, measure wear items
and assess the engine’s parts for re-use. Inspect parts as required (i.e. visual or Magnetic NDT
processes). Refer to the mandatory replacement list given in Section 5 and if applicable,
remove and quarantine any superseded components. Refer also to all the supplementary data
applicable to the engine – such as Service Bulletins and Service Letters. This step is critical for
the overhauler to assess the overall condition of the engine.
Assemble – Re-assemble the engine.
Test Run – A proof run and then running-in is necessary before the overhaul is considered
complete. Running-in may be carried out in the air or, preferably, on a specialised ground-run
stand using special oversized cooling ducts and oil cooler.
Record – The records of the overhaul must be completed, including lists of parts replaced and
the records of the run-in (temperatures, pressures etc).
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3.6

Jabiru 2200 & 3300 Aircraft Engines
Maintainer Requirements
The following are recommended as the minimum requirements for someone carrying out routine
maintenance and inspection on Jabiru Engines.
3.6.1

Jabiru Aircraft Pty Ltd
Facilities
An enclosed workspace with a sealed (i.e. not dirt) floor, adequate lighting, provision of compressed air
and mains electricity. A clean, dust controlled area is required for heavy engine maintenance.
3.6.2 Training
 Completion of an approved instruction course specific to Jabiru Engines. Approved courses include
those offered by Jabiru Aircraft Australia or by local Jabiru Aircraft representatives however completion
of these courses does not guarantee competence. Jabiru training does not override requirements of the
local Airworthiness Authority.
3.6.3 Rating
 Commercial maintainers must hold suitable ratings as required by their local Airworthiness Authority.
3.6.4 Experience
 A minimum of 1 years’ experience working on Jabiru Engines under supervision is recommended for
commercial maintainers before working un-supervised and before undertaking Top End Overhauls,
Total Overhauls, Bulk Strips and other heavy maintenance.
3.7
Overhaul Tools & Equipment
3.7.1 Tool & Gauge Control
 Tool and gauge control is an important part of aviation maintenance systems. Tools and gauges must
be accurate enough for the intended use (i.e. you would not use a 12” steel ruler to measure the
cylinder bore diameter) and be accurately calibrated – for example by an approved laboratory.
 Calibrations must be kept up to date. This means a check calibration every year or more frequently for
regularly used, critical tooling.
 Even quality equipment will wear over time so items like reams, go / no-go gauges and valve seat
cutting tools must periodically be checked to ensure they remain within limits.
3.7.2 Tools:
Access to the following tools will be required:
 Allen keys: 1/4”, 5/32” 3/16” and 3/16” ball end in regular 3/8” drive and “T” handle
 Circlip pliers (internal)
 Crowsfoot: 2” in regular 3/8” drive: 7/16”, ½”
 Hydraulic lifter tool (hydraulic lifter engines only) refer to the drawing in the appendix
 Pliers: long nose, regular square jaw, side cutters
 Ring/open end spanners: 5/16”, 3/8”, 7/16”, 1/2”, 9/16”, 10mm, 17mm
 Ratchet 3/8” drive, breaker bar, 2” extension bar, 3/8”, 7/16”, 1/2” sockets, 7/16” tube socket, 18mm
spark plug socket
 Screwdrivers: flat blade and Phillips head in various sizes
 Feeler gauges: metric and imperial sizes
 Torque wrench: 3/8” drive, “name” brand (Snap-On, Warren & Brown etc), recently calibrated
3.7.3 Equipment:
Access to the following equipment will be required:
 Bench vice with padded jaws
 Calipers: must read up to 180mm
 Degreasing/cleaning system with solvent/solution containment/recycling
 Degree wheel
 Dial indicator and magnetic stand, vee blocks
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Jabiru 2200 & 3300 Aircraft Engines
Hand press
Heat gun or small butane/propane torch with a soft pencil flame
Micrometer and internal measuring tools, must read up to 100mm
Multimeter or an ohmmeter
Spring scale: must read up to 2.5kg in 0.1kg increments
Thread taps: 1/4", 5/16”, 3/8” UNF and UNC
Valve seat cutters: 30°, 45° and 60°
Valve spring compressor, motorcycle type or a ‘G’ clamp with a machined spring cup
3.7.4 General:
 Bearing blue, sometimes referred to as Prussian blue
 Brass drifts, punches, rags, soft mallet, hammers
 Greases: molybdenum disulphide, general purpose
 Loctite compounds: 242/243/262 ThreadLocker, 515 Sealant, 620 Retainer, 7471 Cure Accelerator
 Lubricants: engine oil, Nulon L90
 TorqueSeal brand security marking compound
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3.7.5
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Recommended Sealants Compounds & Lubricants
Figure 4 – Sealants, Compounds & Lubricants #1


Loctite 7471 Cure Accelerator - Loctite 7471 is used where increased cure speed of Loctite anaerobic
products is required. 7471 is particularly recommended when prevailing temperature is low (<15 °C).
Used as a surface prep when very high quality fitting of screws is required.
Nulon Extreme Pressure Anti-Seize Lubricant (L90) offers extremely high film strength and adhesion to
protect moving parts against friction, wear and seizure in all types of extreme conditions. Used to
lubricate parts during assembly, initial start and running.
Figure 5 – Sealants, Compounds & Lubricants #2



Loctite Gasket Maker 515 Flange Sealant is a flexible, gasketing material for use on rigid machined
flanges with less than 0.015"gap.
Loctite Gasket Sealant #2 is a black, reliable, paste-like gasket sealant, dressing, and coating. Sets
more slowly to a pliable film best suited for non-rigid, vibrating assemblies. Used on the induction
manifold.
Bearing Blue – a high colour marking aid which spreads very easily, does not clog or dry out.
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Figure 6 – Sealants, Compounds & Lubricants #4


Loctite C5-A Copper-Based Anti-Seize Lubricant. Prevents corrosion and seizure in high temperature
environments; up to 1800oF (980oC), most commonly used on spark plugs, exhaust bolts, cylinder head
bolts.
Torque Seal F900 anti-tamper compound. Used to mark screw heads, nuts and washers. After setting
becomes brittle so that any movement between these parts is clearly indicated by cracking in the
Torque Seal. Used on many fasteners on the engine and aircraft, including engine through-bolt
fasteners.
Figure 7 – Sealants, Compounds & Lubricants #4





Loctite Gasket Maker 515 Flange Sealant is a flexible, gasketing material for use on rigid machined
flanges with less than 0.015"gap.
Loctite Gasket Eliminator 518 Flange Sealant forms a flexible, solvent-resistant seal that will not tear or
decay. Seals to 300 °F and fills gaps to 0.50". It can be used on flexible metal assemblies, including
aluminum surfaces.
Rubber grease – used to initially fill seals and lubricate rubber parts on assembly – though Nulon L90 is
preferred and generally more effective.
High-temp grease – used to give initial start-up lubrication to many parts of the engine, including the oil
seals.
“Cam Honey” (Molybdenum Disulphide) for cam journals and lobes.
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3.8
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Loctite 620 & Other Retaining Compounds
Figure 8 – Sealants, Compounds & Lubricants #3

Loctite 620 is designed for the bonding of cylindrical fitting parts. Typical applications include locating
pins in radiator assemblies, sleeves into pump housings and bearings in auto transmissions.
Particularly suitable for applications where temperature resistance up to 200°C is required. Used as a
ultra-strong threadlock. Loctite 620 is specified in several places in Jabiru Engine assembly where a
reliable bond is essential. When using it, follow the rules below:
WARNING
-
-
-


Failure to use Loctite 620 correctly can result in engine failure
Check use-by dates. Loctite 620 (like most other compounds used on the engine for sealing etc)
has a use-by date. Generally this is not printed on the bottle but can be found by contacting the
distributor and telling them the batch number.
Work fast. Loctite 620 can cure very quickly. All screws must be torqued to final settings as
quickly as practical. Anything more than a minute is not recommended, particularly if cure
accelerator spray (Loctite 7471) is used.
Only use as much as required/specified. Excess compound can make it nearly impossible to
disassemble the parts later.
Surface preparation is critical. Threads must be cleaned and prepared properly.
To Remove. Can normally be achieved by heating the screw to over 150°C using a pencil-point
gas burner. Minimise direct heat applied to the head of the screw as this can weaken the drive
socket – direct heat towards the thread as must as possible.
Loctite 263 is designed for the permanent locking and sealing of threaded fasteners. Typical
applications include the locking and sealing of large bolts and studs (up to M25 ). A high strength
threadlock.
Loctite 243 is designed for the locking and sealing of threaded fasteners which require normal
disassembly with standard hand tools. Particularly suitable for applications on less active substrates
such as stainless steel and plated surfaces, where disassembly with hand tools is required for servicing.
A medium-strong threadlock. Typically used for cap screws into castings or Aluminium.
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3.8.1 Special Tools
 Special tools can simplify the process and are shown in the photos below.
Figure 9 – Safety Wire / Wire Pliers

Wire used to secure items (nuts, bolts etc) to prevent rotation in service.
Figure 10 – Valve Compressor / Lifter Bleed Tools
Figure 11 – Dimensional Details For Lifter Tool

Used to compress the valve springs, allowing the rocker shaft to be removed and the hydraulic valve
lifters to be bled.
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Figure 12 – Valve Leakage Vacuum Tester

Connected to an air compressor generates a vacuum which is applied to the valve (while closed) to
check for a poorly-sealing valve / seat. See Section 5.11.5 for details of use.
Figure 13 – Valve Spring Compressor / Collet Remover

Modified sash clamp shown (commercial types are also available). Used to compress the valve spring
to allow the collets to be removed from the valve and then the valve to be removed from the head. Also
used for installation.
A screwdriver brazed to a modified spanner. Used to simplify
adjusting the valve clearances in a solid-lifter engine. The spanner
turns the rocker lock nut while the screwdriver turns the adjuster.
Figure 14 – Solid Valve Lifter – Rocker Adjustment Tool
Go-Nogo gauges are used to quickly and accurately check the
inner size of a valve guide. Sizes 7.03 / 7.04 / 7.05 / 7.06 / 7.07 /
7.08. Gauges produced by ‘Prittie’ (www.prittie.com.au) are used
in the factory.
Figure 15 – Valve Guide Size Gauges
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An adaptor is made by welding a compressor air fitting to the
base of an old spark plug. The adaptor is screwed into the spark
plug hole of a head and connected to the leak-down tester to
check the condition of the cylinder assembly.
Figure 16 – Leak Down Tester
Figure 17 – Hand Press & Inserts

A hand press is used to install rocker bushes, distributor shaft and crankshaft seals. Inserts are made
for the press to suit the parts.
Figure 18 – Piston & Ring Installer

Simplifies compressing the piston rings to allow installation of the piston / ring assembly to the cylinder.
Figure 19 – Cylinder Hone Helper

Used during honing with a “Christmas tree” hone to make the base of the cylinder complete. Without
the hone helper the hone would catch on the cylinder skirts. 4” “Christmas tree” hone shown at right.
Note – It is highly recommended that all honing processes required for cylinder barrels be
outsourced to an experienced and reputable machine shop rather than making use of a Christmas
tree hone.
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Figure 20 – Piston Circlip Remover and Installer


Modified screwdrivers shown on left which are used to remove the circlip from the piston.
Tool shown on right which is used to install the circlips to the piston.
Figure 21 – Standard Circlip Pliers

Standard (internal) circlip pliers are required. Such pliers may be modified by brazing a washer to one
leg as shown in Figure 21 (right). The washer is filed down so that it allows the pliers to close only just
far enough to allow the clip to be fitted or removed. This prevents inadvertent over-stressing of the
clips.
An accurate optical tachometer. Reads directly from reflective
strips fitted to the propeller and is used whenever an accurate
check of RPM is required. Will usually read propeller RPM in
sunlight without reflective strips.
Figure 22 – Optical Tachometer
A tool which is used to drill dowel holes in early model
crankshafts and flywheels. Jabiru Service Bulletin JSB012
refers.
Figure 23 – Crankshaft / Flywheel Drilling Jig (for Dowels)
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A degree wheel or degree disc – used during engine assembly to
check engine timing.
Figure 24 – Degree Wheel
Used during initial engine proof runs and / or running-in. Used as a
more accurate gauge to confirm the readings of the standard aircraft
oil pressure gauge. Fitting uses 1/8 NPT thread.
Figure 25 – Supplementary Oil Pressure Gauge
Figure 26 – Crankshaft Run-Out Test Bed

A test bed to simplify measuring crankshaft and propeller flange run-out. This can also be done in a
crankcase half.
Used to test ignition coil
performance.
Figure 27 – Ignition Coil Tester
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Figure 28 – “Finger Bar”

A long lever arm fitted with pins that pit into the propeller flange holes. Allows the crank to be held
easily while tightening or loosening propeller flange or flywheel screws.
Figure 29 – Cam Timing Tool (Hydraulic Lifter)

A piece of material (Nylon has been used here) machined to fit neatly into a hydraulic lifter socket with a
socket in its tip to accept a dial gauge probe. As it sticks out the side of the case (unlike a normal
hydraulic lifter) it is easier to use when checking cam timing.
The tap (at bottom) is used to cut a thread into
the needle seat (small part, middle-left). The
slide hammer (at top) screws into this thread
and is used to draw the needle seat out of the
carburettor. The nylon driver (in centre) is
used to fit the new needle seat to the
carburettor body.
Figure 30 – Carburettor Needle Seat Remover and Installer
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Figure 31 – “Crowsfoot” Adaptors

Commercially available tool designed for high-torque applications on small nuts.
Figure 32 – Crankcase Dry Fit Through-Bolts and Nuts

A set of engine through-bolts, spacers and non-locking nuts used to speed up test assembling of
crankcases to measure bearing clearances etc.
As well as Crankshaft run-in, a dial gauge
is also used to locate top dead centre
(TDC) in the cylinder.
Figure 33 – Dial gauge used to locate TDC
A tool which clamps onto the tip thread of the stud,
holding it tightly and allowing the stud to be screwed out
of the crankcase.
Figure 34 – Crankcase Stud Remover
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An adapted puller used to remove the dowel pins from the
crankcase halves.
Figure 35 – Crankcase Dowel Remover
Essentially a long, large punch used to both remove and
install the welch plugs from the ends of the crankshaft.
Figure 36 – Crankshaft Welch Plug Installer / Remover
Figure 37 – Universal Joint tool FU14B


Snap-On tool FU14B – a universal joint with inbuilt 7/16” nut drive. Used for changing through-bolt nuts
without removing cylinder heads.
FU16B is the equivalent part with ½” socket for use on 7/16” 12-point nuts.
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3.8.2
Jabiru 2200 & 3300 Aircraft Engines
Torque / Tension Wrench
L1
L2
Figure 38 – Torque Wrench & Crowsfoot Adaptor Setting 1
L1
L2 = 0
Figure 39 – Torque Wrench & Crowsfoot Adaptor Setting 2


A good torque wrench is an essential tool for maintaining and overhauling Jabiru Engines. It’s
important to realise however that even the best wrench needs calibrating occasionally. This can be
done using a dead weight on the end of a known arm or – preferably – sending the wrench away to be
calibrated. Note that Civil Aviation Authorities generally require that the tool be calibrated in a way
which is traceable to a NATA-standard laboratory.
A “Crowsfoot” extension as shown in Figure 31 is also necessary – it allows high torque settings to be
used on small nuts without damaging them. The crankcase through bolt nuts used on Jabiru engines
are a good example of an application suitable for a crowsfoot extension. However, when using the
extension as shown in Figure 38 the extra length will throw off the torque setting of the wrench. This
must be corrected using the following formula:
𝐿1
𝐴𝑑𝑗𝑢𝑠𝑡𝑒𝑑 𝑇𝑜𝑟𝑞𝑢𝑒 𝑆𝑒𝑡𝑡𝑖𝑛𝑔 = 𝑅𝑒𝑞𝑢𝑖𝑟𝑒𝑑 𝑇𝑜𝑟𝑞𝑢𝑒 𝑆𝑒𝑡𝑡𝑖𝑛𝑔 × (𝐿1+𝐿2).




L1 is the distance from the middle of the grip of the handle to the centre of the wrench drive lug
L2 is the distance in the direction of the handle from the centre of the wrench drive lug to the centre of
the nut socket of the adaptor.
For example: a nut needs to be tensioned to 30lb.ft. The torque wrench is 12” long and the crowsfoot
extension is 2” long. The extension is oriented as shown in Figure 38. This means that the torque
wrench must be set to:
12
𝐴𝑑𝑗𝑢𝑠𝑡𝑒𝑑 𝑇𝑜𝑟𝑞𝑢𝑒 𝑆𝑒𝑡𝑡𝑖𝑛𝑔 = 30 × (
)
12 + 2
𝐴𝑑𝑗𝑢𝑠𝑡𝑒𝑑 𝑇𝑜𝑟𝑞𝑢𝑒 𝑆𝑒𝑡𝑡𝑖𝑛𝑔 = 30 × 0.857 = 25.7𝑙𝑏. 𝑓𝑡
If the extension is oriented at 90° to the wrench as shown in Figure 39 then no correction is needed
because L2 is zero.
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Corrected Torque Setting Required
No Correction Required.
Figure 40 – Using A Crowsfoot Adaptor
3.8.3




Torque Application Procedure
Good torque application technique is essential if an accurate bolt torque reading is going to be
obtained.
Firstly the nut must be tightened smoothly. Any jerks or bumps can cause the torque reading to be
obtained prematurely.
The torque must be obtained while the nut is turning. If you stop to reposition the torque wrench
and then the required torque reading is obtained without the nut turning, the nut needs to be
loosened a little and then tightened again so the torque reading is obtained while turning.
Unless specified otherwise all torque settings given in this manual are “dry” – i.e. no special
lubricant is applied to the threads or parts. Where directed otherwise it is vital that the directions are
followed exactly.
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3.9
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Safety Wire



Only stainless steel safety wire is used on the Jabiru Aircraft Engine.
There are two methods of safety wiring; the double-twist method that is most commonly used, and
the single-wire method used on screws, bolts, and/or nuts in a closely-spaced or closed-geometrical
pattern such as a triangle, square, rectangle, or circle. The single-wire method may also be used on
parts in electrical systems and in places that are difficult to reach.
When using double-twist method of safety wiring, 0.032 inch minimum diameter wire should be used
on parts that have a hole diameter larger than 0.045 inch (1.1mm). When using the single-wire
method, the largest size wire that the hole will accommodate should be used.
WARNING
Care must be taken not to confuse steel with Aluminium wire.




There are many combinations of safety wiring with certain basic rules common to all applications.
These rules are as follows.
a. When bolts, screws, or other parts are closely grouped, it is more convenient to safety wire them
in series. The number of bolts, nuts, screws, etc., that may be wired together depends on the
application.
b. Drilled boltheads and screws need not be safety wired if installed with self-locking nuts.
c. To prevent failure due to rubbing or vibration, safety wire must be tight after installation.
d. Safety wire must be installed in a manner that will prevent the tendency of the part to loosen.
e. Safety wire must never be over-stressed. Safety wire will break under vibrations if twisted too
tightly. Safety wire must be pulled taut when being twisted, and maintain a light tension when
secured (Figure 42).
f. Safety-wire ends must be bent under and inward toward the part to avoid sharp or projecting
ends, which might present a safety hazard.
g. Safety wire inside a duct or tube must not cross over or obstruct a flow passage when an
alternate routing can be used.
h. Check the units to be safety wired to make sure that they have been correctly torqued, and that
the wiring holes are properly aligned to each other. When there are two or more units, it is
desirable that the holes in the units be aligned to each other. Never over-torque or loosen to
obtain proper alignment of the holes. It should be possible to align the wiring holes when the
bolts are torqued within the specified limits. However, if it is impossible to obtain a proper
alignment of the holes without under-torquing or over-torquing, try another bolt which will permit
proper alignment within the specified torque limits.
i. To prevent mutilation of the twisted section of wire, when using pliers, grasp the wires at the
ends. Safety wire must not be nicked, kinked, or mutilated. Never twist the wire ends off with
pliers; and, when cutting off ends, leave at least four to six complete turns (1/2 to 5/8 inch long)
after the loop. When removing safety wire, never twist the wire off with pliers. Cut the safety wire
close to the hole, exercising caution.
j. Install safety wire where practicable with the wire positioned around the head of the bolt, screw,
or nut, and twisted in such a manner that the loop of the wire fits closely to the contour of the
unit being safety wired.
When using a wire twister (safety wire pliers), grip the wire in the jaws of the wire twister and slide
the outer sleeve down with your thumb to lock the handles or lock the spring-loaded pin.
Pull the knob, and the spiral rod spins and twists the wire.
Squeeze handles together to release wire.
WARNING
When using wire twisters, and the wire extends 3 inches beyond the jaws of the twisters, loosely
wrap the wire around the pliers to prevent whipping and possible personal injury. Excessive
twisting of the wire will weaken the wire.
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Figure 41 – Safety Wire Details
Figure 42 – Safety Wire Installation Using a Twister/Pliers & By Hand
3.10 Hardware

-
Certain applications on the Jabiru Engine must use particular grades of hardware:
Propeller flange attach screws, flywheel attach screws, connecting rod cap screws must be
“Unbrako 1960” or “Brighton Best 1960 Grade” screws in black (not plated) finish.
Where a specific type of hardware is described – i.e. AN4 bolts, ARP 12-point nuts – hardware must
meet the specifications for that type of hardware.
Custom hardware – such as through bolts – must be as described in this manual.
WARNING
Failure to use correct hardware may lead to an unsafe condition.
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Jabiru 2200 & 3300 Aircraft Engines
4 Disassembly Procedure

4.1


4.2




4.3




As each part is removed from the engine it should be set aside for later evaluation – in our factory
engine workshop we use disposable plastic containers to keep all of the smaller components (cap
screws, bolts, nuts, washers, etc) separate during disassembly.
Preliminary Cleaning
Inspect engines carefully before cleaning. The patterns of dirt, oil etc can indicate damage or wear and
provide valuable information of which tasks should be added to the overhaul or inspection process.
The engine must be cleaned externally before it is removed from the aircraft. A stiff-bristled brush,
solvent (de-greaser), water and some compressed air will usually be adequate for this task.
Remove The Engine From The Aircraft
Remove the cowlings and the spinner. Remove the propeller. Disconnect both cables from the battery
and remove the battery from the aircraft. Disconnect the earth cable and free the starter motor power
cable from the wiring loom.
Remove the muffler and then remove the oil drain plug and drain the oil from the engine. Remove the
ram air ducts. Disconnect all engine control cabling and disconnect the air intake duct from the
carburettor. Remove the oil filter, the oil filter adapter and oil cooler.
Disconnect and remove all engine wiring: the signal wiring from the oil pressure and temperature
senders and fuel pressure sender (if fitted), the low-tension ignition wiring and the alternator wiring.
Remove the oil pump from the front of the engine and undo the cap screws that hold the front oil seal
around the crankshaft.
Remove the engine from the airframe and place it onto the engine stand, holding it in place with 3 bolts
through the propeller flange.
Engine Stand
We recommend that an engine stand be used to hold the engine vertically during all workshop
procedures.
In our engine workshop we use a spare propeller flange bolted to the workbench. The propeller flange
on the engine is then bolted to that flange so that the engine is held in an upright position as shown in
Figure 43.
You may find it convenient to simply bolt the propeller flange of the engine directly to the workbench
using 3 suitable bolts.
Note that for a top end overhaul the engine can remain in the aircraft, although the use of an engine
stand may be more convenient and is usually faster.
Figure 43 – Engine Stand
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JEM0001-8
4.4
Jabiru 2200 & 3300 Aircraft Engines
Special Checks Before Disassembly
4.4.1
In-Situ Propeller Flange & Crankshaft Run-Out Measurement
Figure 44 – Measuring Propeller Flange & Crank Run-Out





This procedure is used to gauge the severity of any potential damage to the crankshaft or propeller
flange before carrying out a bulk strip.
Remove one spark plug from each head.
Carefully sand off paint on crank diameter and prop flange where dial indicator will be located. Applying
a little lubricant (such as greaseless lubricant spray) to the area being measured is also recommended.
Position dial indicator onto crank as shown above and eliminate main bearing clearance by bearing
down on crank when rotating. Rotate crankshaft to measure crankshaft run out. 0.01 - 0.03 mm is
normal, but if run out exceeds of 0.08 mm the crankshaft must be replaced.
Position dial indicator onto prop flange as shown above, eliminate end float by either pulling or pushing
flange when rotating. Rotate prop flange to measure the face run out. 0.02 - 0.06 mm is normal, but if
run out exceeds 0.08 mm then the prop flange must be replaced.
4.4.2



Engine Through-Bolt Check
This procedure is used to check if an engine may have fretting of the crankcase halves before
disassembly. This procedure is not suitable for nuts installed with Loctite 620.
Using a calibrated torque wrench, check the lower engine through bolt nuts. Use a torque setting of
28lb.ft for 3/8” bolts or 32lb.ft for 7/16” bolts.
These nuts were originally installed at 30 & 35lb.ft respectively (Table 9), so if the nuts move at the test
torques above it can indicate that the through bolt tension has reduced, possibly due to fretting of the
crankcase halves. If this is found before a top end inspection the overhauler may have to fully strip the
engine – it is recommended that they contact Jabiru Aircraft Australia for guidance.
WARNING
Through-bolts & studs are highly loaded. Never torque nuts above the torque setting given in Table
9 or damage to the bolts will result. Accurate wrench calibration & compensation for any adaptors
used is vital when working on these parts.
The results of this test are an indicator only. False negatives and positives are possible. If in
doubt, disassemble the engine and inspect to be sure.
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Engine Overhaul Manual
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4.5
Jabiru 2200 & 3300 Aircraft Engines
Engine Strip: Complete Overhaul
4.5.1 Accessories
 Remove the spark plugs and exhaust system, followed by the carburettor, the machined inlet manifold
and induction tubes. Remove the starter motor. Remove the distributor caps and high-tension leads,
then the fuel pump, the ignition coils and finally the rear alternator bracing plate to expose the flywheel.
4.5.2


Cylinder Heads And Valve Gear
Remove the rocker covers.
Remove the NPT plug that covers the bottom cylinder head cap screw.
Cap screw under the NPT plug
Remove the valves
Figure 45 – Cylinder Head Disassembly





Where equipped, loosen the hose clamps on the rubber oil line “T” connectors. Loosen and remove
each of the 6 cylinder head cap screws from the cylinder head.
The cylinder head should now be removed from the cylinder along with the pushrod tubes and pushrods
and placed on the workbench. Remove the cap screw from between the rockers and carefully drive the
rocker shaft out of the head, driving it from the non-slotted end.
Remove the rockers.
Using a valve spring tool, compress each valve spring and remove the collets and then remove the
valve springs, spring guides and valves.
Remove the O rings from the pushrod tube holes and the rocker shaft holes. Repeat for each cylinder
head.
4.5.3



Cam Followers, Rocker Oil Lines
Remove the pushrod adapters (hydraulic lifter models only) from the crankcase and use a small hooked
tool (an old dentist’s probe is very useful) to extract each hydraulic lifter.
Remove the cap screw that holds each rocker oil line to the side of the crankcase and remove each
rocker oil line. Remove the O rings from the pushrod and oil line holes.
Undo the retaining grub screw and extract the oil filler tube from between #1 and #3 cylinders.
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4.5.4
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



Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Flywheel Cap Screws
Now the cap screws that hold the flywheel to the crankshaft must be removed.
These cap screws are held in place with Loctite 620, which is very strong, and they will be very difficult
to undo. Great care must be taken not to break any of them or round the drive sockets of the cap
screws. Due to the high stress on the screws and tools the Allen key must be in “as-new” condition with
no wear to its drive faces.
Apply heat to the area around the cap screws, shielding the magnets in the alternator from direct heat,
and then try to crack each cap screw loose using an Allen key and a 3/8” breaker bar.
As excess heat can de-magnetise the alternator magnets overhaulers may prefer to remove the magnet
ring before attempting to remove the flywheel.
This step can take an hour or more and it may involve heating the flywheel (thus the end of the
crankshaft) several times until you can safely undo each cap screw.
Do NOT apply heat directly to the cap screws as this can weaken the screw material. Instead, apply
the heat to the area around the cap screws. This is particularly important because you will need to apply
considerable turning force to undo each cap screw.
It is good practise to wear leather gloves during this task to protect your hands from the heated items
such as the heat shield and the flywheel.
WARNING
Used flywheel cap screws must be discarded and replaced with new items.
Heat shield
Heat the area around the cap screws
Remove distributor drive housings
Figure 46 – Removing Flywheel Cap Screws & Distributor Drive Housings
4.5.5



Distributor Drive Housings
Carefully lever each distributor rotor off of the distributor shaft – the rotors are held in place with 5Minute Araldite and flock so you will need to work each one off gently.
Undo the Allen head cap screws and remove the 2 machined distributor gear drive housings from the
timing case as shown in Figure 46.
Drive the oil seals out of the drive housings.
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4.5.6
Jabiru 2200 & 3300 Aircraft Engines
Flywheel
Lever the flywheel up evenly
Lever on the top of the cap screws
Figure 47 – Removing Flywheel

Once all 6 cap screws have been removed the flywheel can be levered off of the crankshaft: note the
leverage points in Figure 47, where 2 large screwdrivers are placed under the flywheel on the tops of
opposing timing case cap screws and then moved evenly up to provide leverage to remove the flywheel
from the crankshaft.
4.5.7


Timing Case
Remove the cap screws from the timing case and remove the case from the engine mount plate – there
are machined recesses in each side of the timing case, as shown circled in Figure 48, that are designed
to allow a screwdriver tip to be inserted and twisted to break the gasket seal and free the timing case.
A soft hammer may be used to help.
Remove the distributor drive gears and shafts. Drive the oil seal out of the timing case.
Timing case
Distributor
drive shaft
Engine mount plate
Engine mount plate
Figure 48 – Remove Timing Gearbox Case
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Engine Overhaul Manual
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4.5.8


Jabiru 2200 & 3300 Aircraft Engines
Engine Mount Plate And Sump
Remove the cap screws from around the engine mount plate and remove the plate from the crankcase.
Remove the cap screws from around the sump flange and remove the sump.
Figure 49 shows 2 hidden screws which hold the sump to the engine mount plate. These screws can
only be accessed by removing the timing gearbox. Note that these screws have been omitted on later
model engines to allow the sump to be removed without first removing the gearbox.
Figure 49 – Hidden Sump Screws
4.5.9




Starter Motor
Remove clutch housing from starter housing
Remove clutch and bendix gear assembly
To disassemble the starter housing from the drive motor you need to remove the 2 long AN3 bolts.
These bolts are Loctited on assembly and will require heating with a hot air gun onto the starter housing
in the area where the bolts enter the housing. If the Loctite is not heated to soften it, there is a
possibility that the bolts will shear off and a new starter housing will be required.
Older motors used a different starter motor (on left, Figure 50). These motors are undone via Phillipshead screws through the cap of the motor.
Figure 50 – Starter Motor Disassembly
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Jabiru 2200 & 3300 Aircraft Engines
4.5.10 Crankshaft Gear

Once the engine mount plate has been removed the crankshaft gear can be removed from the end of
the crankshaft. Using 2 large screwdrivers, lay one across the end of the crankcase to protect the
surface and use the other to lever the gear off as shown below left, working from side to side.
Crankshaft gear
Extract the crankshaft dowels
Lever the crankshaft gear off
Figure 51 – Removing Crankshaft Timing Gear & Dowels

Extract the 3 dowels from the end of the crankshaft – use a suitable collet type extractor (a
commercially available tool) that has a straight pull as shown above right. It may be necessary to heat
the end of the crankshaft slightly to extract the dowels.
4.5.11 Cylinders
Figure 52 – Remove Cylinders


Undo the base nuts from each cylinder pair until one nut can be removed from the cylinder stud and
then pull each cylinder off of the piston as shown in Figure 52. Note that these through bolts and studs
are normally replaced at overhaul – see Section 5 for details.
Some of the cylinder studs will come away with the cylinders: clamp these studs carefully in the padded
jaws of a vice and remove the remaining base nuts from the studs.
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Engine Overhaul Manual
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Jabiru 2200 & 3300 Aircraft Engines
4.5.12 Pistons
Puller
Remove the circlip
Remove the gudgeon pin
Figure 53 – Remove Pistons


Use 2 small blade screwdrivers to lever out the top gudgeon circlip from each piston as shown in Figure
53. (round type clip shown – use std circlip pliers for circlips with eyes) Now, working on one piston at a
time, support the top of the piston against the side load as shown above right and carefully extract the
gudgeon pin out of the piston.
Remove the piston from the connecting rod. Take care not to put any side load on the connecting rods
while removing the gudgeon pins. A suitable soft drift may also be used to carefully drive the pins out.
4.5.13 Front Seal & Oil Pump Housings
Remove oil pump
Remove screws (8)
Figure 54 – Front Seal & Oil Pump Removal

Before the crankcase can be split the screws holding the front crankshaft seal and the oil pump housing
must be removed. The cap screws holding each must be removed. The oil pump and housing can be
removed completely (a soft hammer may be necessary to break the seal of the housing from the
crankcase). The seal housing cannot be removed completely at this stage but it should be freed from
the crankcase (again, a soft hammer may be necessary).
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Jabiru 2200 & 3300 Aircraft Engines
4.5.14 Oil Return Manifolds


Where equipped, oil return manifolds (Figure 55) are
removed by removing the two retaining cap screws.
Remove all O-rings from the manifolds.
Figure 55 – Oil Return Manifolds
4.5.15 Roller Follower Locking Plate

Where equipped, remove the
roller follower locking plates
from the crankcases.
Locking Plate
Locking plate slot in case
Figure 56 – Crankcase & Locking Plate
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Jabiru 2200 & 3300 Aircraft Engines
4.5.16 Crankcase
Figure 57 – Split Crankcase




Now the crankcase halves can be split: remove the nuts from the retained studs and then set about
carefully tapping each retained stud (located at the front and back of the case) with a suitable soft
hammer until the case halves start to separate.
Carefully pull each case half away from the crankshaft, taking care not to let the camshaft fall. Remove
the camshaft from the case and set it aside.
The oil filler support fitting, arrowed in Figure 57, can be removed now if necessary (i.e. if the case is to
be line-bored). Otherwise it can be left in place.
Remove the main bearing shells. Remove all ‘O’ rings. The front and rear retained studs should be left
in the cases at this stage; if necessary they will be removed after the inspection stage.
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Jabiru 2200 & 3300 Aircraft Engines
4.5.17 Oil Pickup Tube And Strainer




Heat and remove the oil strainer from the oil pickup
tube – gently tapping with a soft hammer will help,
as shown in Figure 58.
Once the strainer has been removed the oil pickup
tube can be carefully tapped back through the
crankcase and removed.
On most engines the oil pickup tube has a swelled
end that seats in the crankcase, however some
older engines may have the oil pickup tube pinned
to the crankcase, so check before attempting to
remove the tube.
Remove the O ring from the pickup tube hole in the
crankcase
Figure 58 – Remove Oil Strainer
4.5.18 Camshaft And Cam Followers


Support the camshaft between the heavily padded jaws of a vice and remove the lockwire and the 4
bolts from the cam gears. Remove the gears and locating pin from the camshaft flange.
Solid lifter engine only: remove the cam followers from each crankcase half.
4.5.19 Connecting rods
Heat the big end cap
Remove the cap screws
Figure 59 – Remove Con-Rods


Remove each connecting rod from the crankshaft in the following matter: heat the big end cap and then
remove each cap screw.
Remove the rod and end cap and the rod and then remove the big end bearing shells.
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
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Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
The caps are located to the rods using 2 off 3mm dowel pins. Care must be taken not to damage these
pins on disassembly.
The brown discolouration of the rods caused by hot oil – this must be removed if the rod is to be subject
to a MPI.
Note that each rod and cap are batch numbered and should be kept in pairs to maintain engine
balance.
4.5.20 Crankshaft

Using a long drift, punch the rear welch plug down until it can be removed from between the rear crank
throws. Figure 60 shows the plug emerging, preceded by some sludge.
Welch plug and debris emerging
Heat and remove cap screws
Figure 60 – Welch Plug & Propeller Flange Removal From Crankshaft



Remove the crankshaft from the stand, clamp it between the heavily padded jaws of a vice and remove
the propeller flange. Once again, heat the end of the crank (and NOT the cap screws) and then remove
each cap screw taking care not to break them in the process.
Lay the crankshaft on the bench and drive the 2 front welch plugs out from the rear – feed a long drift all
the way through the crankshaft and drive both plugs out of the front of the shaft.
Remove the front crankshaft seal housing from the crankshaft and drive the seal out of the housing.
4.5.21 Group The Parts
 This completes the complete overhaul disassembly stage. All parts can now be separated into 2
groups: the discard group, which will contain all of the parts that are subject to mandatory replacement;
and the inspection group, which will be cleaned and inspected prior to being returned to service.
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4.6
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Engine Strip: Top End Overhaul
4.6.1 Accessories
 Remove the spark plugs and the exhaust system, followed by the carburettor, the machined inlet
manifold and induction tubes. Remove the distributor caps and high-tension leads.
4.6.2 Cylinder Heads And Valve Gear
 As for complete overhaul disassembly.
4.6.3 Cylinders
 As for complete overhaul disassembly. Coat the bore of each cylinder with engine oil or a similar
corrosion preventative. After measuring they may be honed lightly.
4.6.4

Pistons
As for complete overhaul disassembly.
4.6.5 Connecting Rods
 As for complete overhaul disassembly. Remove the rod and end cap and remove the bearing shells,
taking care not to drop any parts into the crankcase.
4.6.6 Flywheel & Gear Case
 As for complete overhaul disassembly: Remove the flywheel. Use pliers or similar to remove the rear
seal and replace crank timing gear. Note that it may be necessary to withdraw the dowels from the
crankshaft to allow the gear to be removed. On re-assembly check ignition and cam timing as detailed
below.
4.6.7 Propeller Flange
 As for complete overhaul disassembly. Remove the propeller flange and replace the mounting screws.
4.6.8 Group The Parts
 This completes the top end overhaul disassembly stage. All parts can now be separated into 2 groups:
the discard group, which will contain all of the parts that are subject to mandatory replacement; and the
inspection group, which will be cleaned and inspected prior to being returned to service.
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JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
5 Inspection and assessment
Mandatory Replacement Items – Multi-Cycle Parts
5.1

Certain components have a maximum life of more than 1 or 2 cycles. These parts have a maximum life
as detailed in Table 11

5.2
Mandatory Replacement Items – Full Overhaul
Table 3 – Mandatory Replacement Items – Full Overhaul
Items To Be Checked & Re-Used If Good
Items To Be Replaced
Distributor posts
All necessary mods, plus:
Distributor drive gears
Crankshaft welch plugs
Camshaft Gears
Main bearings
Crankshaft
Thrust Bearings
Camshaft
Connecting rod bearings
Connecting rods
All O rings, gaskets & seals
Propeller flange
Pistons, piston gudgeon pins and circlips
Engine mount plate (engine back plate)
Piston rings
Starter motor and starter motor clutch
Intake and exhaust valves & collets
Carburettor
All nuts, bolts, screws, washers and studs
Ignition coils
Engine through-bolts
Ignition leads
Engine crankcase studs
Valve lifters (solid)
Distributor rotors & distributor caps
Alternator stator & rotor (magnet ring)
Spark plugs
Flywheel & ring gear
Fuel pump
Oil pump assembly
Rubber T – from rocker oil feed line
Exhaust pipes
Connecting rod bolts
Induction manifold & pipes
Oil pump woodruff key
Oil relief valve assembly
Fuel hoses
Sump
Flexible oil hoses
Carburettor rubber mount
All clamps
Crankcase halves
Oil filter
Oil temperature sender
Induction tube joiners
Oil pressure sender
Rocker bushes
Insulating plate on sump
Air filter
Pushrods
Valve lifters (hydraulic)
Pushrod tubes
Crankshaft timing gear
Valve rockers (and adjusters for solid lifter engines)
Valve springs
Oil cooler adaptor
Flywheel Bolts
Engine mount rubbers
Distributor shafts
Cylinder heads – upgrade earlier head types
Valve top spring washers
Cylinders
Rocker shafts
Aluminium flywheel adapter / vacuum pump drive
Steel flywheel starfish adapter
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JEM0001-8
5.3
Jabiru 2200 & 3300 Aircraft Engines
Mandatory Replacement Items – Top End Overhaul
Table 4 – Mandatory Replacement Items – Top End Overhaul
Items To Be Checked & Re-Used If Good
Items To Be Replaced
Crankshaft front seal
All necessary mods, plus:
Valve rockers (and adjusters for solid lifter engines)
Connecting rod bearings
Pushrods
Connecting rod bolts
Pushrod tubes
Intake and exhaust valves
Cylinders: measure & hone.
Pistons, piston gudgeon pins and circlips
Distributor caps
Piston rings
Ignition coils
Cylinder base O rings
Ignition leads
Spark plugs
Fuel pump
Fuel pump gaskets
Cylinder heads
Cylinder head bolts
Valve guides
Induction tube joiners
Carburettor rubber mount
Oil filter
Carburettor – check jetting & float levels
Oil pump O rings
Flexible oil hoses
All cylinder head O rings
Oil pump assembly
All intake & exhaust gaskets
Oil relief valve assembly
All intake & exhaust cap screws
Alternator stator & rotor (magnet ring)
Valve lifters (hydraulic)
Rubber T – from rocker oil feed line
Engine through bolts
Starter motor & starter motor clutch
Crankshaft rear seal
Camshaft (visual check of lobes)
Flywheel cap screws
Crankshaft timing gear
Propeller flange cap screws
Distributor seals
Valve springs
Rocker shafts
Rocker bushes
Distributor rotors
Fuel hoses
Air filter
Aluminium flywheel adapter / vacuum pump drive
Steel flywheel starfish adapter
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5.4


5.5



5.6


Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
General
From this stage on the engine will be divided into separate subassemblies and each subassembly will
be subjected to 3 distinct stages of inspection and assessment:
1. Check for mandatory update items
2. Cleaning
3. Inspection:
a. Visual – scratches, burnt, bent, etc.
b. Dimensional – precise measurements to spec
c. Structural – MPI (Magnetic Particle Inspection) on steel parts
At the end of this process a single parts order can be placed with your local Jabiru dealer.
Mandatory updates
All engines must be checked for mandatory update items – these are intended to bring older engines up
to the current specification and improve reliability and serviceability.
Mandatory updates must be performed during overhaul.
Refer to Section 12 for details.
Mandatory Discard
For some parts there are certain incidents which can result in hidden, internal damage - for example the
crankshaft of an engine which has had a severe prop strike. In these cases the part can be within
tolerances for wear and straightness and even test well with a MPI – but experience has shown that the
part may fail if returned to service.
Any part for which this information is known will have a “Mandatory Discard” note in the inspection
section below.
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JEM0001-8
5.7
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Cleaning
5.7.1 Materials and Processes
 Two processes are involved in cleaning engine parts; degreasing to remove dirt and sludge (soft
carbon) which form the bulk of the cleaning required, and the removal of hard carbon by decarbonizing,
brushing or scraping and grit-blasting.
 In many cases this manual recommends washing parts using Kerosene. In these cases any similar
suitable solvent (such as diesel fuel) may be used at the discretion of the overhauler.
5.7.2 Degreasing
 Degreasing is best accomplished by immersing or flooding the part in kerosene or a suitable
commercial solvent such as Varsol or Perm-A-Chlor and agitating with a brush.
 Overhaulers are warned against the use of any water-mixed degreasing solutions containing caustic
compounds or soap. Such compounds, in addition to being potentially harmful to aluminium, may
become impregnated in the pores of the metal and cause oil foaming when the engine is returned to
service.
5.7.3 Removal of hard carbon
 While the degreasing solution will remove dirt, grease and soft carbon, deposits of hard carbon will
almost invariably remain on some interior surfaces. To facilitate removal, these deposits must first be
loosened by immersion in a decarbonising solution (usually heated). A variety of commercial
decarbonising agents are available, including products such as Redik DKT, Gunk, Penetrol, etc. Only
hydrocarbon based decarbonisers should be used: refer to the note above regarding water-mixed
degreasing solutions.
 Decarbonizing will usually loosen most of the hard carbon deposits remaining after degreasing; the
complete removal of all hard carbon, however, generally requires brushing or scraping. All of these
operations demand care on the part of the mechanic to avoid damage to machined surfaces. In
particular, wire brushes and metal scrapers must never be used on any bearing or contact surface.
 At the conclusion of cleaning operations, rinse the parts in petroleum solvent, water, dry and remove
any loose particles by air blasting. Apply a liberal coating of engine oil or other anti-corrosion product to
all steel surfaces.
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5.8
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Inspection

The inspection of engine parts during overhaul is divided into three categories, visual, dimensional and
structural. The first and last categories deal with the structural defects in parts while the second is
concerned with the size, shape and fit.
Visual inspection should precede all other inspection procedures.
Dimensional inspections should be carried out in accordance with the measurements and tolerances
detailed in the Table of Limits.
Structural integrity of steel components must be determined by MPI (Magnetic Particle Inspection).
5.8.1 Return to service repair work
 Some components will require repair work in order to be returned to service and this work will be
performed as part of the Inspection and assessment stage.
5.8.2 High temperature operation
 The insides of pistons and the crankcase should be visually inspected during disassembly for burnt-on
oil deposits that would indicate overheating and/or operation in extreme conditions.
 If such evidence of overheating is seen then the engine cooling arrangement must be inspected and
possibly modified for greater cooling airflow before the overhauled engine is refitted. The Jabiru Engine
Installation Manuals refer.
5.8.3 Bearing surfaces
 All bearing surfaces should be examined for scoring, galling and wear.
 Some scratching and light scoring of aluminium bearing surfaces in the engine will do no harm and
should not be considered cause for rejection of the part, provided it falls within the tolerances set forth
in the Table of Limits. Even though the part may come within specified limits it should not be
reassembled into the engine unless inspection shows it to be free of other serious defects.
 All journal surfaces should be checked for galling, scores, misalignment and out-of-round condition.
Shafts, pins etc, should be checked for straightness. This may be done in most cases by using vee
blocks and a dial indicator.
5.8.4 Gears
 All gears should be examined for evidence of pitting and excessive wear. Bearing surfaces of all gears
should be free from deep scratches. However, minor abrasions may be dressed out with a fine abrasive
cloth. In particular the starter ring gear and the matching gear from the starter clutch are susceptible to
damage and must be checked carefully.
5.8.5 Corrosion on stressed areas
 Pitted surfaces in highly stressed areas resulting from corrosion can lead to ultimate failure of the part.
The following areas should be carefully examined for evidence of such corrosion: the fillets at the edges
of crankshaft main and journal surfaces, connecting rods and the camshaft.
 If pitting exists on any of the surfaces mentioned to the extent that it cannot be removed by polishing
with crocus cloth or other mild abrasive, the part must be rejected.
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Jabiru 2200 & 3300 Aircraft Engines
5.8.6 Magnetic particle inspection (MPI)
 All steel parts should be inspected by the magnetic particle inspection (MPI) method. The successful
detection of structural failure by magnetic particle inspection demands skill and experience on the part
of operating personnel.
 Too rigid an interpretation may result in the rejection of a sound part, while on the other hand, a part
showing a dangerous indication may be returned to service as a result of a too casual diagnosis. In
general, areas of stress concentration must be watched closely for fatigue cracks. These areas include
such locations as keyways, radii in the corners of the crankshaft, gear teeth, small holes and fillets.
5.8.7 Damaged parts
 Abnormal damage such as burrs, nicks, scratches, scoring, or galling should be removed with a fine oil
stone, crocus cloth, or any similar mildly abrasive substance.
 If scratches or galling are removed from a bearing surface of a journal it should be buffed to a high
finish with a linishing wheel.
 Flanged surfaces that are bent, warped, or nicked may be repaired by lapping to a true surface on a
surface plate. Again the part should be cleaned to be certain that all abrasive has been removed. Pipe
tapped threads (NPT) must not be tapped deeper in order to clean them up, because this practice will
invariably result in an oversized tapped hole.
 Following any repairs of this type, the part should be carefully cleaned in order to be certain that all
abrasive has been removed and then checked with its mating part to assure that the clearances do not
exceed those detailed in the Table of Limits.
5.8.8 Replacement of studs or broken cap screws
 The method of removing studs or broken cap screws depends on the type of stud or cap screw and if it
is intact or broken.
 The procedure for removing studs or broken cap screws is as follows:
1. If there is sufficient thread area available on the stud, use a collet grip tool consisting of a tapered
collet that threads onto the stud and a housing that slips over the collet as shown at right.
Tighten the bolt on top of the housing and draw the collet into the housing to load the puller onto the
stud with a tight grip. Withdraw the stud by turning the housing. Heat may be required to loosen the
Loctite.
2. If a cap screw or stud is broken and there is not enough thread exposed to use the collet type tool,
drill a small hole into the stud using a high-performance drill bit such as a cobalt high speed bit. Use
a pilot bushing to guide the drill into the centre of the stud if it is broken close to or beneath the
surface of the parent metal. Redrill and enlarge the hole to suit the proper size extractor, shown in
Figure 61. Using the extractor, remove the stud. Again, heat may be required to loosen the
Locktite. The RIDGID extractor is available from Ridge Tool Co. of Elyria, Ohio, USA or most tool
suppliers. It is a very effective tool and the only screw extractor recommended by Jabiru Aircraft.
Figure 61 – Stud & Broken Cap Screw Removal
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Engine Overhaul Manual
JEM0001-8
Subassembly A – Crankshaft, propeller flange and connecting rods
5.9
5.9.1
5.9.1.1






Jabiru 2200 & 3300 Aircraft Engines
Crankshaft and propeller flange
Mandatory updates
There are main 2 types of flywheels: alloy centred and the later model steel centred (commonly called
the ‘starfish’ centre).
If you have the alloy centred flywheel, check that the flywheel is dowelled to the crankshaft with 3 x
6mm dowels and retained with 6 x 5/16” x 1¼” UNF cap screws. Crankshafts using ¼” screws for
flywheel retention must be replaced.
Engines with the “starfish” flywheel are retained with 6 x 5/16” x 1” or 6 x 3/8” x 1” UNF cap screws.
The flywheel end of the crankshaft should look like the “5/16”” or “3/8”” photos in Figure 62.
If this is not the case and the flywheel end of your crankshaft looks like the “Old” photo then the
crankshaft and flywheel must be modified before return to service and a new crankshaft timing gear
must be purchased. Details of the process are given in Section 12.4.2.
If the drilling and dowelling modification is required, complete the other cleaning and inspection steps
below to determine if the crankshaft is fit for return to service in all other respects before sending it
away for modification.
Several different length dowels have been used: older flywheels without the “starfish” use 24mm long
dowels. Engines using the “starfish” initially used 20mm long dowels while later versions reverted to
24mm. Refer to Section 13 for serial number ranges. In all cases the dowels are 6mm in diameter.
5/16”
Old
3/8”
Figure 62 – Crankshaft End Detail (Dowel Holes)
5.9.1.2

Any crankshaft which has been subjected to a forced stoppage – for example from a severe prop strike
or piston failure – must be discarded. Section 3.4 refers.
5.9.1.3

Mandatory Discard
Optional Updates: Crank / Propeller Flange
It is strongly recommended that during a full overhaul or bulk strip the engine configuration be updated
to include 8mm dowels between the crankshaft and the propeller flange for those engines not built with
this feature originally. This may require the replacement or modification of the propeller flange and
crankshaft. Refer to Table 40 for S/No. at which this was introduced to production engines.
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5.9.1.4

Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Optional Updates: Starfish Flywheel Adaptor
Current engines use a steel adaptor between the crankshaft and
the flywheel, called a “starfish” because of its shape (shown in
Figure 63). While not mandatory it is strongly recommended that at
overhaul engines are updated to this arrangement. The aluminium
flywheel and alternator rotor are among the parts required for the
update – contact Jabiru Aircraft for details.
Figure 63 – Starfish Flywheel
5.9.1.5




Clean away all paint from the front of the crankshaft and the propeller flange.
Clean out all threaded holes in the ends of the crankshaft with a 5/16” or 3/8” UNF tap as appropriate
then wash and blow out all debris from the holes.
Wash the crankshaft thoroughly with kerosene, taking care to remove all of the sludge from the inside of
the front main bearing: careful use of a small scraper will aid sludge removal. Individually clean each
main to big end oil way drilling using a small brush or similar.
Blow out all of the oil ways, dry the crankshaft and coat with engine oil or other corrosion preventative.
5.9.1.6






Cleaning
Inspection
Inspect the internal face of the propeller flange where the screw heads & washers will seat when
assembled. Ensure this surface is clean of all paint and retaining compound.
The crankshaft and propeller flange must now be checked for straightness: lay the crankshaft between
vee blocks and use a dial indicator on a magnetic base to check that the runout as measured at the
very front of the crankshaft is within the range 0.01 to 0.05mm. Upper limits for crank run-out are given
in Table 10.
Now mount the propeller flange onto the crankshaft with 3 cap screws and position the crankshaft so
that all end float is negated then check the propeller flange for straightness at the outer face of the
flange with the dial gauge.
Typical flange run-out should be in the range of 0.02 - 0.06mm. Upper limits are given in Table 10.
Run-out exceeding these limits would indicate the requirement for a new propeller flange, assuming that
the crankshaft is within tolerance.
Note that this measurement can also be carried out with the crank fitted into a crankcase – provided
that the case is fitted with the front, rear and thrust bearings.
Measure the main and big end journals with a micrometer. The main bearing and big end journals must
measure in the limits given in Table 10. Earlier cranks are 47.918 to 47.938 while later parts are 47.930
to 47.950. Ultimately the clearance between crank and bearings determines if a crank can be re-used.
This must be checked before deciding if a replacement is necessary or not – acceptable clearances are
given in Table 12.
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Jabiru 2200 & 3300 Aircraft Engines
Figure 64 – Crankshaft Measurement






Measurements should be taken at several points around each journal and averaged.
Note that it is unusual to find any significantly out-of-round journals.
Check the oil holes in each journal (main and big end) for a radius. If a radius is not present then use a
fine linishing or polishing wheel to create a radius – there must be no sharp edges that could form a
stress point anywhere on the crankshaft.
Check around the centre holes in the crank web for a radius: once again there must be no sharp edges
that could form a stress point anywhere on the crankshaft. Older engines are more susceptible to this
but new cranks should still be checked.
A polishing wheel in a Dremel can be used to put a radius on the crank centre holes - see Figure 65.
The overhauler must also check all oil galleries in the crankshaft are clear before installation. This can
be done by feeding a piece of steel wire through the galleries. Note that this is also necessary with
brand-new crankshafts to ensure that there is no swarf or other debris lodged in a gallery.
The crankshaft and propeller flange must now be
inspected for structural integrity with MPI (Magnetic
Particle Inspection).
Figure 65 – Radius Crank Centre Holes
5.9.2
5.9.2.1


Connecting rods
Mandatory updates
Connecting rods must be the current machined billet steel type as shown in the photo below.
Older alloy or alloy-steel rods must be replaced with new steel rods.
Figure 66 – Steel Con-Rod
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5.9.2.2





Mandatory Discard
Cleaning
Clean out the threads in the end cap with a 5/16” UNF tap.
Extract the locating pins from the rods and wash out all debris from the holes.
It may be necessary to lightly polish the inner bore of the little end of the rod. A build up of burnt oil or
varnish here can make fitting the gudgeon pin difficult. This can be done by hand using fine emery
paper or using a fine-grade flapper wheel on a die-grinder or Dremel. Only oil deposits must be
removed – not metal.
Wash the connecting rods thoroughly with kerosene and blow dry.
Coat with engine oil or other corrosion preventative.
5.9.2.4

Jabiru 2200 & 3300 Aircraft Engines
In any case where a rod has been subjected to severe loads – for example if the piston struck a valve –
the rod must be discarded.
5.9.2.3



Jabiru Aircraft Pty Ltd
Inspection
Inspect each rod visually for straightness and marking. Note that each rod/end cap pair is marked with a
unique ID number and must only be refitted as a matched pair.
The connecting rods must now be inspected for structural integrity with MPI (Magnetic Particle
Inspection). Note that for MPI the rod must be as clean as possible – usually all burnt oil deposits must
be removed.
The rods must be subjected to a thorough visual inspection for straightness / trueness. As noted
above, any rod which has been subjected to unusual loads must be discarded but otherwise a careful
visual inspection of these parts is sufficient. Uneven bearing wear or abnormal little end wear are
indicators of an untrue rod.
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Jabiru 2200 & 3300 Aircraft Engines
5.10 Subassembly B – Crankcase, camshaft and oil pump
5.10.1 Crankcase
5.10.1.1 Mandatory updates



2mm wide oil channel
Check the rear camshaft bearing in either
case half – there should be an oil channel
2mm wide and 2mm deep running from the
rear main bearing oilway to the rear cam
bearing as shown at right.
If this channel is not present it must be cut into
a case half at this time (only 1 case needs to
be modified – not both).
Clean the case thoroughly after any such
work.
Rear cam journal in the bottom of the left crankcase
Figure 67 – Rear Cam Journal Oil Feed
Rear of the right hand crankcase, behind the back cylinder
Figure 68 – Fuel Pump Oil Drain



Check under the fuel pump drive rod for the presence of an oil return hole through the crankcase wall.
If a hole is not present then position the fuel pump spacer over the stud holes, mark a position near the
bottom of the cavity and drill a 1/8” hole through the crankcase wall as arrowed in the photos above.
Radius each side of the hole and clean away any drilling debris.
Very old 2200 engines did not have a “strainer” fitted to the oil pump pickup. For these engines a
strainer must be fitted at overhaul – this may also require fitting a new oil pump pickup tube.
5.10.1.2 Optional Updates


For hydraulic lifter engines the oil return manifolds shown in Figure 55 can be retrofitted. These parts
improve the oil flow from the rocker chamber in the cylinder head back into the sump. Note that to use
these parts shorter pushrod cover tubes are also required.
Contact Jabiru Aircraft or our local representative for more information
5.10.1.3 Mandatory Discard

In any case where fretting is found all engine through-bolts and studs must be replaced with new items.
This is because fretting is a sign of stress within the crankshaft assembly components and means that
the through-bolts and studs may have been subjected to excessively high loads and fatigue damage.
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Engine Overhaul Manual
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Jabiru 2200 & 3300 Aircraft Engines
5.10.1.4 Cleaning


Clean both crankcase halves thoroughly with kerosene. Remove the front and rear oil gallery NPT plugs
from the left hand case and flush the galleries through. Clean out all threaded holes with the correct
size UNC tap then wash and blow out all debris from the holes. Use a scraper made from Perspex or
similar material to remove any sealing compound from the jointing surfaces.
Blow through all oil galleries and take particular care that absolutely no dirt or debris remains in any part
of the cases. Use a piece of steel wire to push through all oil galleries to check for debris – this is
particularly important if the case has been line bored.
5.10.1.5 Crankcase Inspection and repair
Raised ridge
“Pulled up” metal
Figure 69 – Crankcase Fretting



Inspect the cases for fretting around the main bearing posts. If fretting can be detected (either by
observation and/or by feeling roughness against your fingernail across the affected area – see Figure
69) then it must be corrected by having both case halves surface skimmed and the bearing tunnels
bored to the correct dimensions before return to service.
If fretting has occurred then a complete set of new crankcase studs must be purchased and fitted during
assembly, and the crankcase dowels must be shortened at one end by 0.5mm, then re-radiused / deburred. A detailed explanation of crankcase fretting is included in this manual in Section 12.3.
Clamp the case halves together using the old studs & nuts with 8mm packers under the nuts, torque to
the value given in Table 9 for through bolts (use the value appropriate to the through bolt thread on the
particular engine). Torque in 3 stages, working from the centre studs out to the front & rear studs.
Measure the main bearing and camshaft bore sizes horizontally and vertically as shown in Figure 70.
Figure 70 – Measuring Crankcase Bearing Tunnel


The main bearing tunnel and the camshaft tunnel must both measure within the limits of Table 10. If the
crankcase is not within these tolerances then both case halves must be surface skimmed and the
bearing tunnels line bored to the correct dimensions before the crankcase can be returned to service.
Again note that the target of these measurements is to get the crank – bearing clearance in the target
range (Table 12). Depending on the measurements of the crank etc values outside those listed may
still be acceptable provided that the clearances are within tolerance. Crank-main bearing clearances
and cam-case clearances must be within the limits specified in Table 12.
Where cases have been skimmed the main bearing and cam tunnels must be line bored per Table 10
for correct bearing fit up. This job can only be done by competent machine shop operators.
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Jabiru 2200 & 3300 Aircraft Engines
Figure 71 – Removing Studs and Dowels from Crankcase

If the case is to be surfaced and line-bored then all dowels and studs must be removed from the
crankcase. Use a collet type stud remover to unscrew the retained studs from the crankcase. Gentle
application of heat will assist the removal as shown above. Extract the dowels from the lower stud
holes – in Figure 71 an expanding puller is being used to pull the dowels out of the case. Clean the
stud holes with an M10x1.5 tap (an old stud with grooves cut in the thread to act as a tap may also be
used) and clean and dry the cases.
5.10.1.6 Main Bearings


Examples of main bearing wear are shown below.
Note that the use of automotive oils or oil additives has proven to cause very rapid wear in Jabiru
engines. An air-cooled aero engine is operating at higher power settings and significantly higher
temperatures than a car engine – and Jabiru engines hold less oil than a normal automotive engine.
This puts a lot more pressure on the oil and unless the oil is specifically designed for the application it
can break down, leading to rapid wear of the engine.
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

The upper two bearing shells show severe wear. With wear
this severe Babbit material would have been visible in the
element during an oil filter inspection.
Damage of this sort can be caused by dirty oil, the loss of oil
pressure, use of automotive oil, oil additives or long-term
operation with excessive oil temperatures.

Uneven wear, with the Babbit material exposed.

Normal wear – very little visible wear.
Figure 72 – Main Bearings
5.10.2 Hydraulic Valve Lifters
5.10.2.1 Mandatory Updates

None for engines with solid valve lifters.
5.10.2.2 Mandatory Discard

All Hydraulic valve lifters must be replaced at 1000 hours total time in service.
5.10.2.3 Cleaning – Hydraulic Lifters



If required, the hydraulic lifters can be dismantled and cleaned quite simply using a solvent such as
kerosene. However, extreme care is needed to make sure that each lifter is re-assembled correctly.
The lifters contain many small parts which must be oriented correctly for the valving of the lifter to work.
Note also that different lifters often have subtly different internal parts. Generally, as the lifters are
relatively cheap, it is preferable for the overhauler to fit new parts instead of cleaning the old lifters.
The base of the inside of the lifter tends to accumulate sludge and must be cleaned if it is to be re-used.
Lifters must be cleaned and dried thoroughly before re-installation.
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Figure 73 – Hydraulic Lifter (top left), Solid Lifter (lower left), Roller Follower (right)
5.10.2.4 Inspection



If hydraulic lifters are removed for servicing they must be inspected for wear on the camshaft contact
face. Note that the lifters have a slightly convex (dome-shaped) base. A straight edge placed over the
base (Figure 74) should not quite sit flat on the base – a small gap must be visible at either side. A lifter
which has worn flat must be discarded. The lifter must also be replaced is there is any other adverse
wear of the lifter base – such as galling or pitting of the working surface.
Before installation all hydraulic lifters must be polished around their base as shown below to remove
any burrs and to polish off the sharp corner which can otherwise damage the cam. This is done using a
“Scotch Brite” wheel on a bench grinder or similar – very little material is removed, just enough so that
the corner feels smooth instead of sharp.
Solid lifters require a careful inspection at full overhaul. The camshaft contact face of the solid lifter is
flat and can be checked for wear using a straight edge.
Polish this corner
around the base
of the lifter
Side bleed hole must be
facing up on installation
Figure 74 – Hydraulic Lifter Inspection

Prior to installation hydraulic and roller follower lifters must be primed by injecting oil into the lifter. Nonroller hydraulic lifters must also be installed with the side bleed hole facing upwards. This allows the
lifter to adequately bleed any remaining air during initial running.
5.10.3 Camshaft
5.10.3.1 Mandatory updates


Check the camshaft material (all engines) – solid lifter cams made from a casting (indicated by the
camshaft being hollow) must be replaced with a current billet steel solid lifter camshaft and new lifters.
Check the camshaft identification:
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–
–
–
–
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
solid lifter engine camshafts will have no markings around the front of the cam at all, indicating a
solid lifter camshaft
Hydraulic lifter engine camshafts have 2 dots on the flange and 2 rings around the front of the
camshaft to indicate a hydraulic lifter camshaft. The photos above show a hydraulic lifter (260°
duration, non-roller) camshaft.
If the camshaft in your hydraulic engine has a single ring around the front (285° duration) it must
be replaced with a current 2 ring camshaft and new lifters to suit at overhaul.
Engines equipped with roller followers use a different cam which is not marked with ID rings. This
part can be easily identified by the more rounded shape of the cam lobes (Figure 76)
Figure 75 – 2-Ring Camshaft
Note large tip radius
for roller cam
Figure 76 – Roller Cam Lobe
5.10.3.2 Cleaning



Clean out the 4 threaded holes in the rear flange with a 1/4” UNF tap.
Clean the camshaft with kerosene and dry.
Coat with engine oil or other corrosion preventative.
5.10.3.3 Inspection



Visually inspect the lobes for any abnormal wear patterns and any chipping around the sides of the
lobes. Any chipping or signs of wear through the hardened surface will require a new camshaft. Inspect
the lifters for signs of wear on the face. If replacing the camshaft the lifters must also be replaced.
The camshaft and the camshaft drive gears must now be inspected for structural integrity with MPI
(Magnetic Particle Inspection).
The overhauler must be aware that of the different types and combinations of camshafts and lifters
fitted to Jabiru engines over the years currently only three combinations are approved: a solid lifter
(zero ring) cam with solid lifters, a hydraulic lifter (260° duration, 2-ring) cam for hydraulic lifters and a
roller follower cam (rounded lobes) for roller follower engines. Engines with other configurations must
be updated to an approved configuration at overhaul.
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5.10.4 Oil pump
5.10.4.1 Mandatory updates
Inlet port.
1
Outlet port.
Indentations
2
3
Figure 77 – Port Plate Evolution



Jabiru Service Bulletin JSB004 also refers to this part. The original design for the oil pump port plate
could suffer from cavitation which in turn caused pressure spikes and damage to the oil cooler. During
overhaul old oil pumps must be modified as detailed below or have a new port plate fitted.
Figure 77 above shows 3 different styles of oil pump port plate.
- Plate #1: This is the original design, with the port plate outline unbroken by indentations.
- Plate #2: This is an intermediate design. At the top of the outlet port and at the bottom of both ports
there are small tapered indentations. Some versions of this plate will only have the larger
indentation at the top of the outlet port, and not the pair at the bottom. Again, this design plate must
be reworked to be equivalent to Plate #3.
- Plate #3: This is the current plate design. The small indentations have been replaced by a large
tapered cut at the top of the inlet port. Changes have also been made to the other side of the plate
(which faces the crank cases) to remove sharp edges & reduce cavitation.
Plates like Plate #1 & Plate #2 can be modified to be equivalent to Plate #3. Where the plate already
has the indentation on the top of the outlet port, care must be taken to leave at least 2mm between it
and the end of the new cut on the inlet side.
New Cut
Figure 78 – Modified Port Details


This work can be carried out by hand using a Die Grinder or similar tool. Jabiru Aircraft can provide a
1:1 template if required. This work requires the disassembly of the oil pump and should only be carried
out by an approved person with appropriate skills.
Alternatively a new port plate may be fitted.
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5.10.4.2 Cleaning


Wash the pump rotors and housing thoroughly with kerosene and dry.
Coat the pump rotors with engine oil or other corrosion preventative.
5.10.4.3 Inspection







Inspect visually for any signs of wear or damage to the rotor surfaces.
Visually inspect the woodruff key which drives the pump. It is normal for there to be some light marking
on this part, however significantly marked keys must be replaced.
Measure the clearances between the parts and ensure they are within the limits given in Table 12.
Note that oil pump gears must be replaced as a set.
Replace any components that fail to meet these requirements.
Note that the inner and outer rotors each have a machined alignment marking as shown arrowed in
Figure 79. These alignment markings must both face up when the rotors are in the housing.
Note also that the alignment markings will move in relation to each other as the inner rotor rotates in
relation to the outer rotor.
Figure 79 – Inspecting Oil Pump
5.10.5 Oil Pressure Relief Valve
5.10.5.1 Mandatory updates
Figure 80 – Oil Pressure Relief Valve
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Relief poppets manufactured from brass must be replaced with steel items as they can wear at an
accelerated rate.
5.10.5.2 Cleaning


The oil pressure relief valve assembly is located underneath the oil filter / oil cooler adaptor on the side
of the crankcase as shown in Figure 80.
Wash the components of the valve thoroughly with kerosene and dry.
5.10.5.3 Inspection


Visually inspect the poppet for wear. If it has a significant worn ring where it has been sitting against
the washer then the marks must be polished out or the poppet replaced.
Take note of the number of washers fitted under the relief valve spring – fitting more washers is a
method of adjusting the average oil pressure of the engine – more washers = higher oil pressure. For a
solid lifter engine high oil pressure is not a problem (within the set limits) however a hydraulic lifter
engine needs mid-range oil pressure to operate properly. This will be adjusted during the engine test
run. AN4 type washers are used with 1 being fitted as standard during factory assembly. Up to 3 can
be used – more than 3 will result in coil-binding of the spring and relief valve malfunctions. Valve
function can be checked by depressing the poppet and to ensure it can move off the seating washer.
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5.11 Subassembly C – Pistons, cylinders and cylinder heads
5.11.1 Pistons and cylinders


Complete overhaul: mandatory replacement of pistons, piston rings, gudgeon pins and piston circlips.
Cylinders may require replacement as after honing if they do not have enough wear left to complete
another cycle. Note that a light, quick hone is generally all that is required.
Top end overhaul: mandatory replacement of pistons, piston rings and piston circlips.
5.11.1.1 Mandatory updates
Cylinder Length
Figure 81 – Measuring Cylinder Length


Top end overhaul: measure the length of the cylinders and any shims fitted – combined cylinder/shim
length must be within the limits given in Table 10 when measured from the base flange to the top of the
bore as shown above.
Shorter cylinders must be replaced with longer cylinders. Alternatively 1.00mm or 0.50mm shims may
be cut to suit the base of the cylinder and fitted between the cylinder and the crankcase. Note that only
1 shim can be fitted to any barrel – for example fitting 2 off 0.5mm shims to increase the barrel
assembly length by 1mm is not acceptable. This distance is used to set the compression ratio of the
engine and short cylinders give higher compression with reduced detonation tolerance.
WARNING
On no account may cylinders or cylinder / shim assemblies shorter than the minimum length given
in Table 10 be used.
5.11.1.2 Cleaning


Top End Overhaul / Full Overhaul: Pistons are to be replaced.
If conducting maintenance: clean the pistons in a decarbonising solution. Clean the ring lands out
carefully using a non-metallic scraper – a piece of Perspex is often useful for this task. A piece of
broken piston ring can be used with extreme care but is not recommended because of the damage to
the piston which may result – any other type of metal scraper is discouraged for the same reasons.
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
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Take care not to scratch the base or sides of the ring lands – this will inhibit ring sealing which may lead
to blow by and other related problems. Wash the pistons with kerosene then soapy water, rinse and dry.
Clean the cylinders thoroughly with kerosene, dry and apply engine oil or other corrosion protection to
the bores immediately.
After measuring, if a cylinder is deemed fit for re-use it should be lightly honed. Cylinders outside the
limits given in Table 10 at the mid-bore are unfit for re-use.
5.11.1.3 Inspection and repair

Note that whenever measuring cylinders or pistons measurements must be made both in the line of the
gudgeon and at 90 degrees – as shown in Figure 82 (right). This is because wear of these parts is
usually higher in one orientation than the other.
Figure 82 – Measuring Cylinders & Pistons










Top End Overhaul / Full Overhaul: New pistons are to be fitted.
Measure the cylinder diameters at approximately half stroke; for a top end overhaul they must not
exceed the limits noted in Table 10 to be to be returned to service. A cylinder which measures smaller
than this measurement will give 1 to 2 cycles further use if operated and maintained correctly. After
measuring, check carefully for signs of ovality: measure at 3 equally spaced intervals around the bore.
Measure the piston diameter and calculate the clearance between the cylinder wall and the piston: it
must be within the limits given in Table 12 in order for the piston and cylinder combination to be
returned to service.
If the clearance is greater outside the limits given in Table 12, new cylinders must be fitted.
During Other Maintenance: Check the side clearance of the top 2 rings (the gap between the side of
the ring and the ring land on the piston). If the side clearance is outside the limits given in Table 12 new
pistons must be ordered.
Note that recent pistons incorporate an increased ring sliding clearance of 0.05mm to 0.10mm. Wire
circlips on the gudgeon pin were also replaced with standard 25mm ID circlips at this time. 23mm
internal circlips are also used on some engines.
Full Overhaul:
Measure the cylinder diameters at approximately half stroke; for a full overhaul they must not exceed
the limits noted in Table 10 to be to be returned to service. A cylinder which measures smaller than this
measurement will give 2 cycles further use if operated and maintained correctly. After measuring,
check carefully for signs of ovality: measure at 3 equally spaced intervals around the bore.
Measure the piston diameter and calculate the clearance between the cylinder wall and the piston: it
must be within the limits given in Table 12 in order for the piston and cylinder combination to be
returned to service.
If the clearance is greater outside the limits given in Table 12, then parts must be changed – pistons or
cylinders – to obtain correct clearance.
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
If returning the cylinders to service, bead blast the outer cylinder area (fins and cylinder base) to
remove all old paint and rust, then etch prime and paint with a high-temperature paint.

The bores must then be lightly honed with a Sunnen
brand MM33-J58 stone or equivalent so that a 30-40°
crosshatch pattern is visible in the bore as shown in
the drawing at right.
This will allow the new rings to bed in quickly and
minimise oil consumption for the rest of the cycle.
Run a 5/16” UNF tap through the head bolt threads to
clean any debris out that might cause incorrect torque
readings.
Wash the cylinder thoroughly with kerosene and then
hot soapy water, rinse, dry and coat the bore with
engine oil or other corrosion protection immediately.



Figure 83 – Cylinder hone Pattern
5.11.1.4 Weighing


Weigh piston / connecting rod / gudgeon pin / circlip / piston ring assemblies.
Verify that each assembly falls within the limits given in Table 10.
5.11.2 Cylinder heads


Complete Overhaul: mandatory replacement of cylinder head bolts, valves and collets.
Top End Overhaul: mandatory replacement of cylinder head bolts and valve collets.
5.11.2.1 Mandatory updates

Top end Overhaul: Older cylinder heads should be upgraded to the current “fine fin” model.
5.11.2.2 Cleaning


Top End Overhaul: Run a 12mm tap through the spark plug threads.
Clean the cylinder heads: bead blast the combustion chambers and valve seats.
5.11.2.3 Inspection and repair


Top End Overhaul: Check for cracks between the valve seats and for movement of the valve seats in
the cylinder head. Also check for cracking around the exhaust manifold stud threads. Dye penetrant
testing may be required.
Figure 84 (right) is a cylinder head in which the cylinder has crushed into the cylinder head. This can
be caused by over-tensioning or operating the engine with too-high CHT’s. This is not acceptable for
re-use as it alters the engines compression ratio.
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Figure 84 – Cracking Between Valves, Recessed Cylinder Spigot
5.11.3 Valves



Top End Overhaul: Visually inspect each valve for any signs damage: this may include burnt seats,
scoring of the stem or necking of the stem. This is a useful check as it will indicate very poor
maintenance. Valves are replaced at both top end and full overhauls.
Check that the heads of the valves protrude into the combustion chamber by the amount indicated in
the drawing below – if the heads of the valves are recessed into the roof of the combustion chamber
then new cylinder heads must be fitted. It is recommended that overhaulers do not attempt to replace
the valve seats in the heads as this job requires special tools and extreme temperature differences.
If refacing is required the inlet and exhaust faces should both be ground to 45°. Both valve and seat
face have a parallel contact of 45° - there is no undercutting.
Figure 85 – Valve Measuring
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5.11.3.1 Inspection and repair
Figure 86 – Valve Damage

Figure 86 shows various types of valve damage. From left to right they are:
1. Valve stem necking caused by the exhaust valve operating for some time with poor sealing. The
exhaust gas leaking past the seat overheated the valve stem with the result as shown.
2. A valve showing burnt residue on the valve seal face and rust on the valve stem from incorrect long
term storage.
3. A non-sealing valve.
4. A badly burnt valve – this has run for many hours, allowing the exhaust gas to burn away the
sealing face.
5. A failed valve. This can occur due to the valve sticking and being struck by the piston (intake valve)
or by the valve being overheated and cracking (exhaust valve).
WARNING
Damage caused by valve sealing is a progressive process. If caught early the fix will be simple and
cheap – if allowed to develop the repairs can be major and expensive.

As a part of the daily inspection the engine must be turned over (or “pulled through”) by hand while it is
cold. This allows the operator to feel the compression of each cylinder in turn and assess if any
cylinder is leaking. Tests like this will normally catch a poorly sealing valve before damage becomes
critical.
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5.11.4 Valve guides
GO-NOGO GUIDES
(SUCH AS THOSE
MADE BY PRITTIE)
Figure 87 – Valve Guides




Top End Overhaul:
Use a micrometer to measure the valve stems and the valve guide bores and calculate the clearance: it
must be within the limits set in Table 12. If the clearance is greater than this then new valve guides
must be purchased and fitted.
Note that the values given above are maximums – there is no point returning a cylinder head to service
if it has valve guides already worn close to the maximum allowable – before the engine has completed
its next cycle the guides will be unserviceable. Refer also to Section 12 for details.
It is unusual for guides to need to be replaced after 1 cycle (1000 hours) however it can happen.
Figure 88 – Measure Guide Wear (Telescopic Gauge Left & Middle, Go-No-Go Gauge Right)


An alternate method for measuring valve guides is to use a Go- No Go gauge as shown in Figure 88.
The gauges must be machined very accurately to the required size. Gauges sizes of 7.04, 7.05, 7.06,
7.07mm etc are recommended. Figure 15 also shows these tools.
We strongly recommend having a specialist fit the new valve guides.
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
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




Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Heat the cylinder head evenly (using an oven or other uniform heat source) until the old guides can be
driven out easily.
If the head is not heated sufficiently it is possible that some metal may be picked up when the old
guides are driven out, so aim to achieve a temperature of approximately 150°C for this operation.
Once the old guides have been removed allow the head to cool naturally before sizing the holes to fit
the new guides.
Ream the valve guide holes out carefully if required until a 0.03 - 0.05mm interference fit is obtained
and then heat the head again while cooling the guides in a plastic bag in the freezer for at least an hour.
Then, working quickly, drive each guide home using a suitable tool with the head supported on an
inclined base, all as shown in Figure 87.
Make sure that the oil hole in each guide is facing up when fitted.
Reaming the guide bore to the new build value set in Table 10.
If new valve guides are fitted then the valve seats will need to be recut.
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5.11.5 Valve seats


Top end overhaul: apply bearing blue to the valve and rotate the valve against the valve seat using
hand pressure only. Remove the valve and inspect for sealing between the valve and the seat – if there
is not a uniform seal within the limits shown in Figure 89 then the seats will need to be cut and the
valves may also need to be refaced.
Valve seats are cut at 45 degrees for the actual seat and then under and over cut at 30 and 60 degrees
as required to obtain a seat width as shown in Figure 89. In general, try to cut only the minimum amount
from each seat in order to extend the life of cylinder heads.
Figure 89 – Valve Seat Geometry
5.11.5.1 Inspection and repair
Figure 90 – Recessed Valve Seat, Valve Being Cut



The valve face must protrude at least 0.6mm (inlet) or 1.0mm (exhaust) from the face of the combustion
chamber.
Figure 90 (left) shows a valve fitted to a recessed seat. This assembly is unserviceable. To avoid this,
valve seats must be cut as lightly as possible.
Figure 90 (2 right pictures, above) shows a valve / valve seat being cut using a hand grinder and valve
lapping paste on the sealing face.
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After cutting the seal of the valves must be checked using a vacuum tester. This can be done without
fitting the valve springs as the vacuum which is applied in this test holds the valve against the seat.
Figure 91 shows a vacuum test rig. This system connects to the workshop’s compressed air supply
and uses a venturi effect within the silver box (right) to generate a partial vacuum. A fitting must be
made to connect the vacuum tube to the cylinder head – we use a layer of insertion rubber to seal
between the metal fitting and the cylinder head. Once operating the vacuum is assessed via a gauge.
If the valve achieves 25inhg or less then the valve must be cut against the seat to improve the seal.
Again, remember that the seats and valves must be cut as little as possible.
Alternatively the seal can be checked using bearing blue, assessment of the lapping marks or by using
liquids to look for leaks. Vacuum is the preferred method as it is fast, clean and accurate. The unit
pictured below used compressed air to generate a vacuum and is manufactured by SMC, P/No. ZH13B.
Figure 91 – Vacuum Test Rig


If the valve seats are badly worn or recessed into the cylinder head then a new cylinder head must be
fitted or new seats must be fitted to the old head. However, replacing the valve seats is a specialist
task which we recommend that overhaulers do not attempt as it requires special tools and extreme
temperature differences.
Note that the hydraulic valve lifters have an internal piston with approximately 4.0mm of total travel ±2.0mm from the original set position. This allows these engines to automatically adjust for up to this
amount of variation in the valve train. Variations larger than this can lead to incorrect valve actuation
and engine damage. Valve recession, cylinder head recession and similar factors all affect this
measurement and must be monitored carefully during overhaul. Shorter length pushrods are available
for hydraulic lifter engines to address this, however they are normally not required if the engine is
overhauled using the guidelines given within this manual. Note that fitting shims to the engine will have
the same effect on the lifter as using a shorter pushrod – i.e. the piston in the lifter will run higher in the
bore. Accordingly the effect of using shorter pushrods can also be gained by fitting longer cylinders or
cylinder shims. Normal valve tip to rocker clearance with lifter fully bled is around 1.8 / 1.9mm. With
later shortened pushrods of 215mm, add 1.0mm to above dimensions.
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5.11.6 Cylinder Head – Cylinder Seal
Figure 92 – Valves Assembly, Cylinder Head / Cylinder Lapping
5.11.6.1 Inspection and repair



If second-hand cylinder heads are being used they must be lapped to seal onto the cylinder spigot. The
process is similar to grinding a valve – valve grinding paste is applied to the cylinder spigot and the
head rotated against it. An old, unservicable cylinder, held in a vice, should be used for this task. This
step is not necessary with new heads. Figure 92 refers.
A visual check will show when the surfaces are mated / lapped properly. As per the valves, care should
be taken to remove the minimum amount of material.
After lapping the valves or head must be cleaned thoroughly to make sure all the grinding paste has
been removed.
5.11.7 Valve Springs, Spring Washers & Pushrods

Complete Overhaul: mandatory replacement of valve springs
5.11.7.1 Mandatory updates



The valve springs used for hydraulic lifter engines are different to those used in solid lifter engines.
Note that the spring designed for the hydraulic lifter engine can also be used on solid lifter engines.
Pushrods are different lengths for hydraulic and solid lifter engines.
Acceptable pushrod lengths are given in Table 10.
5.11.7.2 Inspection and repair



Top End Overhaul: Measure the valve spring lengths as shown in Figure 93 – each spring must
measure within the limits set in Table 10 to be returned to service. If any springs are shorter than this
then order a complete new set of valve springs – if a few are short then tension will be down for all
springs.
Check both ends of the springs for sharp edges or burrs which could damage the valve spring washers.
Sharp edges and burrs should be polished off.
Inspect valve spring washers (top and bottom) for wear. Worn parts must be replaced. Measure top
spring washer thickness – minimum thickness 1.3mm.
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Jabiru 2200 & 3300 Aircraft Engines
Figure 93 – Valve Springs, Pushrods
Thicknes
s
Figure 94 – Valve Spring Washer Thickness





Check the pushrods for straightness: use vee blocks & dial gauge or check by rolling the rods along a
piece of thick flat glass. Check the pushrod ends for signs of wear or damage. The photo above-middle
shows a badly worn pushrod end on the left compared to a good pushrod end on the right. Replace any
bent or damaged pushrods. Pushrod length limits are given in Table 10. For hydraulic lifter engines the
215mm type is recommended for standard use as it allows greater tolerance to wear in the valve train.
Later engines use hollow pushrods to lubricate the rocker gear (Figure 93, right). Again, the 215mm
long part is recommended.
Engines equipped with roller followers use a different length hollow pushrod – as detailed in Table 10.
Check the pushrod cover tubes for straightness and smoothness: during final assembly these slide
through the O rings in the cylinder heads and any roughness may rip the O rings, so this would be a
very good time to polish the outside of each pushrod tube and replace any bent or damaged tubes.
Pushrod tubes must be checked for wear at the O ring seal (Figure 95). Wear or damage here will
cause oil leaks and must be polished out or the tube replaced.
Figure 95 – Pushrod Tube End
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5.11.8 Rockers
5.11.8.1 Mandatory updates

Engines being converted to pushrod oil feed must use new lifters, pushrods, rockers and rocker bushes
as detailed below.
5.11.8.2 Inspection and repair
Split joint
Bush
Oil hole in bush
Rocker arm
Figure 96 – Fitting Rocker Bush








Measure the rocker shafts and the rocker bushes and calculate the clearance – ensure it is within the
limits given in Table 10. Bushes are replaced during a full overhaul. If the clearance is greater that this
limit then new rocker bushes must be ordered.
Use a hand press to push the old bushes out with the new bushes, making sure that the split joint in
each bush is oriented towards the top of the rocker as shown in Figure 96 (left). Typically the inner size
of fresh bushes is around 12.06mm.
Note that for engines using the hollow pushrod oil feed there must be an oil hole in the rocker bush as
shown in Figure 96 (right). If this hole is not present rapid wear of the bush will occur.
Push the new bushes completely into each rocker – the width of the bush determines the amount of end
float for the rocker.
Rocker shafts must be inspected for serviceability. Check for scoring etc – slight imperfections can be
polished out – larger damage requires the replacement of the shaft. Shafts measure 11.98mm when
new. If using a shaft with slight wear it can be inserted into the head from the other direction which
places the worn section on top of the shaft where it will not wear anymore or affect rocker operation.
In all engines the rocker end which presses against the valve stem must be checked for wear. In some
cases this face may require polishing to remove defects.
For engines using the hollow pushrod lubrication system the valve rockers are equipped with an oilway
running from the pushrod socket to the tip of the rocker (see Figure 97). This oilway also feeds into a
groove in the bush installation bore. At overhaul or when new parts are fitted these oilways must be
inspected visually and using a fine probe (such as a 1.0mm drill bit) to ensure they are open and free of
obstructions. After probing blow the oilways out with compressed air to shift any debris.
In solid valve lifter engines the rocker adjusters & lock nuts must also be examined & assessed for wear
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Oilways
Oilway
Figure 97 – Solid VS Hollow Valve Rockers
5.12 Subassembly D – Sump & Induction Manifold
5.12.1 Sump
5.12.1.1 Mandatory Updates
Oil temperature
sensor
Oil drain
New 2200 sump
Old 2200 sump
Figure 98 – 2200 Engine Sumps
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Jabiru 2200 & 3300 Aircraft Engines
Figure 99 – 3300 Engine Sumps



Very old type 2200 & 3300 engines used sumps where the induction manifold was cast as a part of the
sump, with the intake tubes exiting the manifold at 90°. These sumps must be replaced with a newer
type at overhaul.
2200 engines: check the sump type – the older, finned sump is smaller, while the new, larger sump has
no fins. Finned sumps on 2200 hydraulic lifter engines must be replaced with the current model, larger
sump. This will reduce crankcase pressure and excessive blow-by of engine oil into the overflow bottle.
Either sump may be used on a solid lifter engine. Note that although the sump volume was increased
the oil capacity stayed the same. Different oil cooler mounting brackets are required for each sump.
3300 engines: two types of sumps, shown in Figure 99, are acceptable for use. Note the intake tubes
leaving the manifold at an angle.
5.12.1.2 Cleaning

Remove drain plug and temperature sensor and clean threads. Use a scraper made from Perspex or
similar
material
to
remove
any
sealing
compound
from
the
jointing
surfaces.
Clean the sump with kerosene and dry. Blow out all holes.
5.12.1.3 Inspection And Repair


Inspect the sump for any signs of cracking around the bolt holes on the flange, and check the threads in
the drain and temperature sensor mounting holes.
Check your dipstick length against the limits given in Table 10: Measure from the top of the dipstick
handle to the Full and Low marks.
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5.12.2 Induction Manifold
5.12.2.1 Mandatory Updates

There are no mandatory updates to the induction manifold assembly.
5.12.2.2 Optional Updates



2200 engines: Early 2200 engines had the induction manifold cast as part of the sump & were equipped
with a 32mm carburettor. It is recommended to fit a new sump & 40mm carburettor at overhaul.
3300 engines:
- Most 3300 engines are equipped with a bolt-on induction manifold assembly similar in appearance
to the 2200 engine part shown in Figure 185 (note the shape of the diffuser used in this part –
circled in the figure).
- Later engines use a “Series III” bolt-on induction manifold assembly. This system incorporates two
round diffusers into the manifold body in place of the “airfoil” shaped part shown in Figure 185. It
also uses different angles and shapes for the induction pipes themselves.
- Current engines use an induction cast into the sump as shown in Figure 99 (right).
All of these configurations are acceptable for the 3300 engine: upgrades in this area at overhaul are
optional.
5.12.2.3 Cleaning

Disassemble and wash. Note that to remove the Loctite sealing compound it may be necessary to use
a plastic scraper and / or scouring pad.
5.12.2.4 Inspection And Repair

Visually inspect.
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5.13 Subassembly E – Flywheel, Ignition Coils, Starter Motor And Alternator
5.13.1 Ignition Coils & Alternator
5.13.1.1 Mandatory Updates




Flywheel – must be dowelled to the crankshaft with 6mm dowels and 5/16” or 3/8” (not ¼”) cap screws
– refer to Subassembly A (Section 5.9) for details of this modification. Note that early “Starfish” type
flywheel used 20mm long dowels while the previous assembly and the current version “Starfish” use
24mm.
Ignition coils: Shiny black coils marked “LEADING X” must be replaced.
Alternator: 3-phase alternators must be replaced.
Tachometer: sensors must be “hall effect” type or read from two dedicated tags fitted to the flywheel.
Senders which read directly from the starter ring gear teeth must be replaced.
5.13.1.2 Cleaning


Clean the flywheel with kerosene and dry.
Wipe all electrical components with a soft cloth; use a brush if necessary to dislodge dust from each
unit. Do not use chemical cleaners on any electrical components.
5.13.1.3 Inspection And Repair








Inspect the starter drive gear and the flywheel ring gear for chipped teeth: if any teeth are chipped or
missing then a new gear must be ordered. The ring gear may have either 99 or 101 teeth – you must
specify the exact tooth count when reordering either gear. Note also that the engine backing plate is
specific for each ring gear – i.e. a 99-tooth-compatible backing plate must be used with a 99 tooth ring
gear and vice versa for a 101 tooth part.
Magneto and alternator magnets must be tested using a prop bolt attached to a spring balance. Details
of the testing method and the required limits are given in Section 9.6.
Magnets that are weaker than this must be replaced. When replacing magnets the North (N) pole must
be oriented outwards on the flywheel. It is very rare for magnets to lose their strength but it can happen
if the magnets are overheated or subject to an impact.
Test the ignition coils as detailed in Section 9.6.
Test the resistance between the alternator poles and the resistance to ground as detailed in Section
9.6.
Replace any units that fail to meet these values.
Visually inspect the alternator for signs of burning, rubbing, chafing or other damage. Replace if
damage is found. Disassembly is only required if damage is found.
In particular inspect the connectors on the output wires from the alternator. If there are indications of
excess heat these connectors must be removed and new, high-quality insulated female connectors
fitted. Ensure the new connectors are a tight fit when test-assembled with a male connector.
Figure 100 – Different Ignition Coil Models (Honda on Left, Jabiru on Right).
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Jabiru 2200 & 3300 Aircraft Engines
5.13.2 Flywheel/Starfish Attachment



Inspect the fit of the dowels between the crankshaft and flywheel:
- Normally the dowels will remain in the crankshaft when the flywheel and gear are removed. If any
dowels come out of the crank assess the fit by inserting a new dowel: the correct fit of dowel into
crank is an interference fit: the parts require a firm tap from a copper hammer to assemble.
- Assess the fit of the dowels into the crank timing gear: a mild interference fit where the parts can be
assembled by light hammer taps is the minimum acceptable fit.
- Where equipped, assess the fit of the dowels into the flywheel spacer / vacuum pump drive: a slip fit
where the parts can be assembled by hand but no movement can be felt between the parts is the
minimum acceptable fit.
- Assess the fit of the dowels into the flywheel (or starfish, where equipped). An interference fit where
the parts must be assembled by firm hammer taps is the minimum acceptable fit.
Unacceptably loose fits require the replacement of parts.
Inspect the condition of the flywheel attachment holes. Figure 101 shows a “Starfish” which was
damaged by a prop strike: it can be seen that the screw and dowel holes are elongated. This part must
be replaced. Elongation can be checked by placing a tapered round item in each hole – such as a
suitably sized punch or pen – to identify any damage.
Figure 101 – Damaged Flywheel “Starfish”
5.13.3 Starter Motor
5.13.3.1 Mandatory Updates

Older (Black) starter motors were less powerful. It is recommended that these be replaced at overhaul.
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Figure 102 – Starter Motor Old & New
5.13.3.2 Cleaning

Clean and wash all parts in solvent except the motor. Clean the motor by wiping with a clean rag to
remove dust and metal particles. Clean the commutator with a soft brush and a fast drying solvent
(Figure 104, left).
5.13.3.3 Inspection And Repair





Check commutator for wear, if you are not experienced in this field then seek a suitable qualified person
to check the commutator for serviceability.
Check brushes for wear, if you are not experienced in this field then seek a suitable qualified person to
check the brushes for serviceability, replace if they are less than 10 mm long.
Check bendix gear for chipped or missing teeth, and that the clutch slides freely on the shaft, replace if
necessary.
Check the ball bearings on the motor rotor for serviceability, replace if necessary (Figure 104, right),
using a suitable puller to remove the old part.
Check the bushes at each end of the clutch and bendix gear for wear and replace as required, lubricate
the bushes with grease.
Figure 103 – Typical Disassembled Starter Motor
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Figure 104 – Starter Motor Overhauling
5.13.4 Engine Mount Plate
5.13.4.1 Mandatory Updates


As noted above, engine mount plates are specific to the flywheel ring gear used – there are 99 and 101
tooth versions of the plate to suit the different gears. Parts must be matched on assembly.
Note that the 2200 mount plate is shorter (vertically) than the 3300 plate.
5.13.4.2 Inspection And Repair
Figure 105 – Checking Engine Mount Plate Trueness


Check to ensure the plate being inspected is suitable for use on the engine – matching the ring gear
and the engine model.
Using a straight edge, carefully check the plate in both directions for trueness. Often an engine which
has been in an accident or had a severe propeller strike will be bent. Figure 105 refers
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5.14 Subassembly F – Gear case and distributors
5.14.1 Gear Case & Distributors
Broached cutaway
Distributor gear
Figure 106 – Distributor Gears & Case
5.14.1.1 Mandatory Updates

Check the inner boss of the main timing gear case around the distributor drives for a broached cutaway
as shown arrowed in yellow above left. If this cutaway is not present it must be ground into the case
before it can be returned to service. Use a Dremel tool with a cutting burr or a hand file to make the
cutaway as shown above left: it should measure 12mm wide and 3mm deep when complete. This must
be done for both distributors.
5.14.1.2 Cleaning



Scrape all gasket material from the timing case flange with a Perspex scraper.
Check that all threads are clean – use a tap if necessary.
Clean all components thoroughly with kerosene and dry.
5.14.1.3 Inspection and Repair







Check the rivets that hold the distributor gears to the shafts as shown above right and replace any that
are loose with new 3/16” x 5/16” Monel rivets, taking care to drive the pin out of the centre of the rivet
on completion of fitting.
Check gears and gear teeth for any marks or scoring.
Check the shafts for corrosion and seal marking and polish as required. Measure the distributor shaft to
bearing clearance: it must be within the limits of Table 12 to be returned to service.
If deep score marks (from the seal) are present (as shown in Figure 106 – right) the shaft must be
replaced.
Check the interior of the distributor cap, looking for cracks, corrosion and making sure that the carbon
brush in the centre of the cap is fitted and in good condition.
Check the high-tension leads and replace any which have chafing or other damage. Damage needing
replacement is rare, however chafing must be guarded against carefully.
Check the fit of the high-tension lead caps onto the distributor and spark plugs. Visually check the
metal contacts inside the caps. If the fit is loose or if the contact is visibly damaged as shown in Figure
107 then a screwdriver or similar must be used to re-shape the contact (it should be round) and to resize it for a better fit – for a spark plug the diameter of the contact needs to be reduced to tighten while
for a distributor cap it needs to be expanded. Each cap should fit with a clear “click” as it connects to the
distributor cap or spark plug.
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Figure 107 – Adjusting High Tension Lead Caps
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5.15 Subassembly G – Fuel Pump And Carburettor
5.15.1 Carburettor
5.15.1.1 Mandatory Updates

Check the carburettor for current tuning and jetting using the table below:
Table 5 – Carburettor Tuning
SOLID
LIFTER
2200
HYDRAULIC
SOLID
LIFTER
3300
HYDRAULIC






NEEDLE
JET
MAIN
JET
IDLE
JET
NEEDLE
32mm
Bing
2.68
2.70
2.72
2.35
0.45
Std circlip
2nd from
bottom
40mm
Bing
2.76
2.78
2.80
40mm
Economy
2.80
2.25
2.35
0.45
Economy
needle
40mm
Economy
2.90
2.45
0.45
Swelled type
40mm
Bing
40mm
Economy
40mm
Economy
2.50
2.55
0.35
0.45
0.35
2.80
2.80
0.45
0.35
2.85
2.55
0.45
2.85
2.90
2.55
2.60
0.35
0.45
Std circlip
2nd from
bottom
Std circlip
2nd from
bottom
Economy
needle
Std circlip
2nd from
bottom
Swelled type
Order any replacement parts required to achieve current carburettor tuning standards.
Refer also to Jabiru Service Bulletin JSB018. In some applications non-standard jets will be required
and are acceptable if their use is based on proper testing.
To improve cold starting the choke jet may be enlarged. Drilling to 1.2mm is recommended for
Australian applications. The choke jet is located in the bowl as shown in Figure 108 (left).
To improve the engine’s idle the idle jet port must be drilled out to 1.6mm. This is done at the factory
during assembly but is worth checking at overhaul. Figure 108 (right) shows the drilling being done by
hand. Note the air nozzle blowing into the idle jet to force the aluminium shavings from the drill out of
the carburettor.
New fuel hose must be fitted.
The float bowl needle seat must be checked. 3300 engines use a 2.4mm diameter, specially shaped
orifice in this part while the 2200 engine uses 2.0mm – though the 2.4mm seat is also acceptable for
2200 applications. Figure 30 shows the tools needed to change the seat which is located in the
carburettor body above the float needle. As noted at Figure 30, if the seat is to be changed a tap is
used to remove the old part and a special nylon drift used to install the new. More details of this
process are included in Section Figure 112.
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Choke jet fitted at base of bowl
Air nozzle
Tang for
adjusting
float level
Figure 108 – Carburettor Updates
5.15.1.2 Cleaning




On initial disassembly, check for contamination like that shown in Figure 108 (left). Contamination like
this will be an early indicator for increased wear in the engine and will warn the overhauler to check
thoroughly for wear on parts like cylinders.
The carburettor exterior can be cleaned using kerosene, then washed with water and air dried.
The carburettor interior can be cleaned using a carburettor cleaner aerosol – with the exception of the
diaphragm. The diaphragm can be carefully washed using warm soapy water.
Blow out all passageways using compressed air.
5.15.1.3 Inspection and repair
Diaphragm spring
Diaphragm
Needle carrier
Air density sense port
Needle
Atomiser
Idle circuit inlet
aperture
Air density sense port
Throttle butterfly
Needle Jet
Idle mixture screw
Float needle valve
seat
Float needle valve
Jet Carrier
Main Jet
Idle Jet
Figure 109 – Carburettor Schematic
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Remove cap screws
Figure 110 – Disassembling Carburettor #1
Idle jet
Idle screw
Choke Jet Tube
Main/Needle Jets
Figure 111 – Disassembling Carburettor #2


Remove the upper cap of the carburettor and inspect the rubber diaphragm for any cracking, perishing
or other damage. Hold the diaphragm up to a strong light and carefully stretching each section in turn.
If any leaks are found then a new diaphragm must be ordered. Lift the slide and diaphragm assembly
out of the carburettor body, remove the needle (using a flat-bladed screwdriver, Figure 111 left) and
inspect the condition of the parts, checking the needle for wear and to determine if it is the current
design.
Remove the float bowl, floats, needle valve and jets. Hold each jet up to the light to check that it is
clean. Particularly check for varnish which can form inside the jet, reducing its internal size. This
varnish can normally be removed easily using an aerosol carburettor cleaner. Do not use drills or wire
to clean jets as this can alter their internal size and affect the engine tuning.
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JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
Using thread tap to remove old seat
Fitting new seat using Nylon tool
Figure 112 – Fitting New Float Needle Seat

The float bowl needle seat must be checked. 3300 engines use a 2.4mm diameter, specially shaped
orifice in this part while the 2200 engine uses 2.0mm (though the 2200 can also use a 2.4mm seat if
required). Figure 30 shows the tools needed to change the seat which is located in the carburettor
body above the float needle. As noted at Figure 30, if the seat is to be changed a tap is used to remove
the old part and a special nylon drift used to install the new.
Needle
Jet
Atomiser
Main Jet
Jet
Carrier
Washer
Figure 113 – Carburettor Jets & Diaphragm





During re-assembly ensure that the atomiser, needle jet, jet carrier, washer and main jet are installed in
the correct orientation and correct order as shown in Figure 113 (left). Also ensure that the tag on the
diaphragm is aligned and fitted correctly to the socket in the carburettor body as shown in Figure 113
(right)
Check the idle mixture screw. Screw fully in then screw it out 1 turn for 2200 and 3300 engines. The
idle screw is shown in Figure 111.
The float level must be set at 11-13mm down from the lip of the bowl. Adjust the brass tang of the float
as required. An alternate setting method is to turn the electric fuel pump on and lift the floats, noting at
what float height the flow cuts off.
Carefully check the condition of the rubber coupling between the carburettor and the engine.
Particularly on installations where a “pod” filter is used this coupling can crack – and the cracks can be
hard to spot.
Set the throttle butterfly idle stop so that the butterfly is just cracked. This setting will then need to be
confirmed during the engine test run.
5.15.2 Fuel Pump
5.15.2.1 Inspection & Repair

Top End Overhaul: check fuel pump diaphragms and gaskets, replace as required.
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JEM0001-8



Jabiru 2200 & 3300 Aircraft Engines
Complete Overhaul: replace fuel pump and gaskets complete.
Two different fuel pumps have been used on Jabiru Engines – as shown in Figure 114. Note the cast
emblems on the top of the pump on the left – this is a Type 1 pump while the other is a Type 2. Both
pumps are driven by pushrods acting from a special lobe of the camshaft, however the Type 2 pump
requires a different length pushrod to the Type 1: refer to Table 10 for lengths.
Wherever a Type 1 pump is replaced with a Type 2 the pump pushrod must also be replaced.
Figure 114 – Fuel Pumps (Type 1 on Left, Type 2 on Right)
5.16 Subassembly H – Final Assembly
5.16.1 Exhaust System
5.16.1.1 Mandatory Updates

Engines equipped with exhausts which require gaskets between the manifold and the cylinder head are
recommended to be replaced with non-gasket exhaust systems at overhaul.
5.16.1.2 Inspection & Repair




Visually inspect the entire system for cracks, dents and wear.
Inspect sealing faces for damage such as gas erosion.
Spring tags that are excessively worn must be replaced.
Systems that show signs of excess leakage must be adjusted or replaced.
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JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
6 Assembly – Top-End Overhaul
6.1



6.2

6.3







General
Those parts which must be replaced during a top end overhaul are detailed in Section 5.3
Those parts of an engine which have been disassembled for a Top-End overhaul are to be assembled
in accordance with the details given in the full overhaul assembly part of this manual.
Special top end overhaul build sheets are given in Section 9.
Engine Through-Bolts
As a pre-emptive test the engine through-bolts may be checked as detailed in Section 4.4.2. If fretting
is suspected it may be necessary to fully strip the engine to have the cases “decked” and line-bored.
Note that fretting can lead to failures of the engine through bolts and engine stoppage – so suspected
case fretting must be taken seriously.
Fuel Pump
For a top end overhaul the fuel pump must be inspected.
Measure the push rod which drives the pump from the camshaft. Its length must be within the limits set
in Table 10 and the ends must be in good condition – no excess wear, scoring etc.
Remove the cap of the pump and visually check that the internal parts are in good condition – no tears
or cracking in the diaphragms or rust on the spring. Re-assemble.
Pre-lube the pushrod using a small amount of grease.
New gaskets must be used when re-fitting the pump. All joints must have 1 face coated with Loctite
515 sealant.
Apply Loctite 243 to the 5/16 x 1 1/4” cap screws and tighten to the value given in Table 9.
Assemble the connecting rods, cylinders, piston and cylinder head assemblies in accordance with the
full overhaul procedures detailed in Section 7 below.
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Jabiru 2200 & 3300 Aircraft Engines
7 Assembly – Full Overhaul







Once all parts have been inspected and all required new parts have been obtained then the assembly
process can begin.
The process described here will be to complete each subassembly stage first and then the final stage
will be described in Subassembly H – Final assembly (Section 7.8), where each of the subassemblies
will be combined to form the complete overhauled engine.
Remember that for a Jabiru Engine it is required that at certain stages of the assembly a second person
check the work and sign the build sheet to verify that it has been done correctly.
Prior to starting the assembly process, take the time to thoroughly clean your work area – wash the
workbench and engine stand down, clean all of your tools and make sure that you have everything that
will be required before starting work.
Check the engine configuration against Section 12 for mandatory updates.
Keep your work area sealed against dust and dirt ingress and cover all work in progress with a clean
cloth or seal in a plastic bag between operations.
For critical fasteners torque specifications are given in Table 9. Table 9 also gives generic torque
values for other applications.
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7.1.1


Jabiru 2200 & 3300 Aircraft Engines
Subassembly A – Crankshaft, propeller flange and connecting rods
7.1

Jabiru Aircraft Pty Ltd
Crankshaft, propeller flange
Before beginning assembly ensure that the crank and propeller flange have been checked for run-out
(see Section 4.4.1).
Fit the 3 welch plugs to the crankshaft. All of the welch plugs should be expanded slightly before fitting.
The plugs and the areas in the crankshaft where they will be fitted must be cleaned with Loctite 7471
cure accelerator and then have a few drops of Loctite 620 Retainer applied around the inside of the
crankshaft and the outside of the plug before fitting.
Cleanliness is essential when using Loctite!
#1
Figure 115 – Crankshaft Painting, Degree Wheel




Start with the front 7/8” plug, located at the back of the front double main bearing, driving the plug in
from the rear, then the rear 7/8” plug at the back of the crankshaft and finally the 28mm front plug
located at the very front of the crankshaft – tap each plug squarely into place using a suitable sized drift
or punch: a very long 3/8” drive extension can be used for the front 7/8” plug. The front and rear welch
plugs should be tapped ¼” in from the face of the crankshaft, so that their outside lip sits about 1mm in
from the face of the crank.
Mask the oil seal bearing surface on the front of the crankshaft and paint the front end of the crankshaft
with a suitable paint (Figure 115 Left – note masking tape visible on seal face). Paint the propeller
flange at the same time. When painting these parts always take care not to paint any mating faces or
faces where screw heads will bear.
Fit the propeller flange temporarily and mount the crankshaft vertically to the workbench/engine stand
on top of a degree wheel, with the #1 big end journal pointing at the 90 degree before top dead centre
(BTDC) mark on the degree wheel as shown at Figure 115, (right). i.e. set up so that TDC faces the
assembler’s chest and #1 big end points to the left.
Note that the propeller flange will be finally fitted after the front crankshaft seal housing has been fitted
when the engine is removed from the workbench/engine stand.
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7.1.2
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Connecting rods
Blue the back of the shells
Torque the big end cap screws
Figure 116 – Blueing Bearings, Assembling Rods


Apply bearing blue to the back of the big end shells and fit them to the rods, hold the connecting rod in
the padded jaws of a vice and tighten the cap screws to 18 ft lb in 2 stages.
Loosen one big end cap screw then measure the bearing crush as the gap between the other side of
the rod and the bearing cap with a feeler gauge. Bearing crush should be in the range given in Table
12. If the bearing crush exceeds these limits it can be corrected by carefully sanding the ends of the
bearing shells on a sheet of 600 grit sandpaper laid on a flat surface and then rechecking. Remember
that altering bearing crush will also alter the big end size slightly, so it must be re-measured after
adjusting the crush. Also note that the critical parameter to be considered is the bearing-crank
clearance. In most cases it is best to check the clearances first and then confirm acceptable crush.
Measure the bearing crush
Measure the big end size
Figure 117 – Measuring Connecting Rods

Retighten the cap screws to 18 ft lb then measure and record the big end size of each connecting rod
and each big end journal. Calculate the big end bearing clearance. If necessary, move the connecting
rods from one journal to another until you get a uniform clearance in the range given in Table 12.
Record the clearances on the build sheet. A typical crankshaft journal will measure around 45.00mm,
requiring a typical big end bearing inner diameter of 45.04 – 45.06mm (see Table 10 for details). Again
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Jabiru 2200 & 3300 Aircraft Engines
the clearance between bearing and journal is the critical thing and must be in the range given in Table
12. If the clearance is too large then in some cases the bearing can be carefully sanded by rubbing the
ends of the bearing shells on a sheet of 600 grit sandpaper laid on a flat surface – though bearing crush
must be maintained. If the clearance is too small a different shell or rod may be tried which gives a
better fit.
WARNING





It is imperative that these tolerances are achieved.
Mark each connecting rod with the journal/cylinder number for later refitting. Remember that oil
pressure is directly controlled by the sum of the bearing clearances, so take the extra time to obtain
uniform clearances across all connecting rod/big end journal combinations.
Remove the bearing shells and check the blue on the back for contact – there must be at least 90%
surface contact between the back of the bearing shell and the connecting rod.
Check the clearance of the gudgeon pins in the small end of each connecting rod. It may be nessesary
to hone the bore of this hole to achieve correct fit. This requires skill and special tools. It is highly
recommended that this task be outsourced to a reputable machine shop. Inexperience or use of
incorrect tool will likely create a fit which is too loose, making the connecting rod unservicable.
Clean the bearing shells and connecting rods carefully before final fitting. Clean the cap screws and the
threads in the bearing caps using a 5/16” tap, then Loctite 7471 cure accelerator and allow to dry.
Weight of reciprocating parts must be as detailed in Section 5.11.1.4. Extra care must be taken if a
partial set of pistons are to be fitted – i.e. 1 new piston to an engine. In this case the weight of the new
piston must be compared to to the weight of the existing pistons.
7.1.3
Assemble
Fit the connecting rod
Check for ease of rotation
Figure 118 – Fit Connecting Rods



Fit the bearing shells to each connecting rod and it’s respective bearing cap: apply a smear of Nulon
L90 to the bearing surface and the journal and fit the rod and bearing cap to the crankshaft with the
dowel side of the connecting rod facing towards the rear of the engine (towards the flywheel). Engine
oil should also be applied to the connection.
Press the rod and the bearing cap together by hand or gently with a pair of multigrips. This must be
done to seal the connection between cap and rod – if the cap is not fitted against the rod when Loctite is
applied to the threads then a small amount of the retaining compound can find its way between the
mating surfaces, holding them slightly apart and altering the fit of the rod to the crank. This can lead to
excess clearance between the rod and crank – which is not acceptable.
Apply a smear of Loctite 620 Retainer to the first 3 threads of each cap screw and the first 3 threads in
the bearing cap then fit each pair of cap screws and tighten initially to 10 ft lbs then to the final value
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

Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
given in Table 9. Perform a final check for ease of rotation: the connecting rod should move smoothly
around the big end journal.
If it does not rotate freely then the rod should be removed and inspected. Scuffing of the bearing
surfaces near the join between cap and rod will require that the connecting rod can be fully
disassembled and the big end polished in the areas adjacent to the join between rod and cap. If there
is no particular scuffing pattern then the crankshaft journal should be polished before refitting the rod
with new cap screws and retesting. In cases like this also check that the crank journal remains round.
Wipe away any excess Loctite from the end of the cap screws when fitting is complete. Note that any
excess Loctite left on these parts can harden, then break free and be carried to the oil pressure relief
valve, causing oil pressure problems later.
WARNING
Loctite and other compounds can cure quickly at times. Overhaulers must work steadily to ensure
all treated connections are tightened fully before the compound cures.


Recheck the torque for each cap screw before fitting the next connecting rod.
If the crankshaft and connecting rods assembly will be left exposed for more than an hour or so the
entire assembly should be oiled lightly and covered with a plastic bag or wrapped with a clean cloth to
prevent corrosion or dirt from taking hold.
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Subassembly B – Crankcase and camshaft
7.2
7.2.1
Crankcase
Short front crankcase studs: 52mm min
Long front and rear crankcase studs: 95mm min
Figure 119 – Crankcase Assembly Preparation



Lubricate and fit the O rings to the bottom main bearing stud holes (arrowed in Figure 119 - left) and
then fit the front and rear crankcase studs using Loctite 620 Retainer: clean and prime the threads first
using Loctite 7471 cure accelerator. Use a collet type stud tool to screw the 2 short front crankcase
studs to a free length of 52mm and the 2 long front and the 2 rear crankcase studs to a free length of
95mm as shown in Figure 119. Note: Later longer studs are positioned 54mm and 97mm free length
above the crankcase join.
Fit the hollow dowels to one crankcase half in the positions arrowed above. It is vital that poorly fitted
dowels are not used at the crankcase join – if the dowels can be pushed in by hand then they are too
loose. The correct fit it a light “tap” fit using a soft hammer. Oversize dowels are available to ensure a
snug fit. These are identified by “dots” machined into them as shown in Figure 120 – the standard size
has no dots then the size increases progressively up to the 3-dot dowel which is the largest size
available. Experience in Australia has shown that 1-dot dowels are suitable for most overhauled
engines with 2-dot and 3-dot parts being used very occasionally.
The overhauler may opt to fit somewhat loose-fitting dowels for temporary assembly of the engine to
measure bearing sizes. This simplifies sebsequent disassembly. Where such parts are used they must
be clearly marked so that they are not fitted to an engine during final assembly by mistake.
WARNING
Ensure correct size dowels are used for final assembly.
Figure 120 – Crankcase Dowels
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Jabiru 2200 & 3300 Aircraft Engines
Case clamping equipment
Bearing blue to joining
surfaces
Figure 121 – Crankcase Clamping Preparation






Apply bearing blue to one joining surface of a crankcase half and under the main bearing shells, fit the
dowels and main bearing shells and fit the crankcase halves together.
The oil filler tube is fitted to the right crankcase now or later during final assembly.
Clamp the case halves using the old studs and nuts with 8mm packers under the nuts. Torque to the
value given in Table 9 (as appropriate to the bolt size) in 3 stages, working from the centre studs out to
the front and rear studs. Measure the main bearing bore size with the new main bearing shells in place.
The bore size with the new main bearing shells in place must be within the limits given in Table 10
when measured directly across between the case halves.
The diameter of the main crankshaft journals subtracted from this bearing inner diameter gives the
bearing clearance. Clearances must be within the limits given in Table 12.
Disassemble the case halves & check for 90% surface contact on the back of the bearing shells &
across all jointing surfaces. Clean off the bearing blue with some kerosene or suitable solvent on a
clean cloth & refit the bearing shells to the main bearing bores. Apply a light coating of oil to the shells.
Thrust bearing
Thrust bearing fitted to case
Figure 122 – Fitting Thrust Bearings

Fit the thrust washers to the machined positions either side of the second front main bearing: use some
general purpose grease to hold them in place.
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


Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Offer one half of the crankcase up to the crankshaft.
Fit a dial gauge on a magnetic base to the top of the
crankshaft and measure the end float of the
crankcase half on the crankshaft by moving the
crankcase half up and down by hand. End float must
be within the limits of Table 12 – 0.25mm is typical.
Record the value (alternatively feeler gauges may be
used). Remove the case from the crankshaft and set
aside until final assembly. Fit the oil pickup tube O
ring to the crankcase, then fit the oil pickup tube from
the front of the case. The oil strainer housing is then
Loctited to the pickup tube using Loctite 620. Note
that the strainer must face forwards / down as
shown.
Figure 123 – Fitting Oil Pickup Tube
Fit solid lifters to the lifter bores in the case, lubricating each lifter stem and holding each lifter in place
with a small amount of grease under the head. The camshaft will hold the solid lifters in one half of the
case in place during fitting. Once the case is joined it is impossible to fit or remove solid lifters.
Lubricate the base of the lifters and the cam lobes using moly grease or cam honey. This prevents
damage during initial starting of the engine.
Hydraulic lifters will be fitted later in the final assembly process as they can be fitted from outside the
case.
Measure crankshaft end float
Fit solid lifters in crankcase
Figure 124 – Checking Crankshaft End Float, Installing Solid Lifters
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7.2.2
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Camshaft
Figure 125 – Cam Timing Gear Assembly



Clamp the camshaft between the heavily padded jaws of a vice and fit the large inner gear, the alloy
spacer and the small outer gear to the flange at the rear of the camshaft: clean and prime 4 new AN4H5A bolts and the cam flange threads with Loctite 7471 cure accelerator, align the inner gear so that
the alignment hole on the camshaft flange aligns with the hole in the inner gear.
Hold that position and fit the spacer and the outer gear as shown in the drawing above and secure in
place with the AN4 bolts with Loctite 620 Retainer applied to the threads. Torque the value given in
Table 9 and lockwire the bolts in place in pairs as shown above left (also refer to Section 3.9).
Oil the cam bearing surfaces and then place the camshaft into one half of the crankcase and check for
end float between the rear flange and the rear housing with feeler gauges as shown below (right). Value
measured must be within the limits given in Table 12 (around 0.10mm is typical). Record the value.
Lockwire camshaft bolts
Check camshaft end float
Figure 126 – Assembling Cam & Fitting to Crankcase
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In this subassembly task the piston rings will be gapped and fitted to the piston, the front gudgeon pin
circlip will be fitted to the piston and finally the piston will be inserted into the cylinder ready for later final
fitting to the connecting rod.
7.3.1


Jabiru 2200 & 3300 Aircraft Engines
Subassembly C – Pistons, cylinders and cylinder heads
7.3

Jabiru Aircraft Pty Ltd
Pistons
Several different variations of piston have been used in Jabiru engines. In some instances it may be
required to partially replace an engine’s pistons (i.e. replacing 2 pistons in a 4-cylinder engine) during
maintenance. In this case the overhauler must accurately weigh reciprocating part assemblies per
Section 5.11.1.4.
For in-service maintenance purposes it is acceptable practice to fit piston assemblies in pairs – i.e.
pistons #1 and #2 may weigh 529g and 530g respectively while pistons #3 and #4 weigh 533g and
532g. However where possible it is recommended that all reciprocating assemblies be weight matched.
Where all pistons in an engine are replaced the limits detailed in Section 5.11.1.4 apply.
Figure 127 – Thrust Direction Markings For Pistons

Current pistons feature modifications to the piston crown to allow
the piston to prevent a stuck valve impacting the piston.
Assembly for these parts is the same as for older piston types and
is as detailed herein. However, note that these parts are handed
– with a different part number being used on the left side of the
engine compared to the right. When confirming piston orientation
note that the valve relief is always on the sump side of the engine
as shown in Figure 128.
Figure 128 – Installation of Pistons With Valve Relief
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
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Looking at the underside of the piston there is a cast-in lump on one gudgeon pin housing (see Figure
127). This lump must be fitted to the engine on the side of the connecting rod closest to the propeller
flange. Another marking used for the same job is a small arrow or indent cast into the crown. The
arrow must point towards the propeller flange and/or the indent must be on the propeller flange side of
the connecting rod. These markings show the correct orientation of the piston to the thrust loads from
combustion relative to the propeller.
Figure 129 – Fitting Circlip to Piston
Figure 130 – Fitting Wire-Type Piston Circlips


Fit wire-type circlip:
- Many engines use a wire circlip in place of the part shown in Figure 129. Installation of that type of
clip is shown in Figure 130.
- The circlip has a lot of tension and as a result installation can be tricky.
- Overhaulers must roll the clip into the groove – they must never be levered in as this can damage
the piston or the clip.
- Take care not to scratch or burr the piston or to bend the clip itself.
- As the clip slips into the groove, listen for a crisp “snap” sound, indicating that it has dropped fully
into place. Always give the installed clip a close inspection after installation. Use a small
screwdriver or pick to check that it is tightly in place – in the case of the piston, apply an “opening”
load to the ends of the clip, expanding it into the groove. The clip should not move and should not
spin in the piston. If in doubt, fit a replacement.
Fit conventional circlip:
- Both 25mm and 23mm internal circlips have been used in Jabiru engines, as shown in Figure 129.
- Visually inspect the clips supplied and identify the “flat” and “round” sides. Figure 131 shows the
two different sides of a typical clip – note the sharp corners on the top of the left clip while the clip on
the right has a rounded top face and rounded corners. This comes from the clip manufacturing
process and will be apparent in all clips of this type – one side will be “sharp” and the other “round”.
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JEM0001-8
-
-
-
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
The clips must be installed so that the “rounded” side faces the item being retained (the gudgeon
pin in this case). See Figure 132 for an illustration of the correct and incorrect orientation. A clip
that is installed the wrong way won’t be able to carry as much load and will fail more easily.
When fitting the clip, take care to compress it by the bare minimum amount required. DO NOT
compress the clip until the eyes touch. Over-compressing will permanently damage the clip: Figure
133 shows a clip which was over-compressed lying on top of a brand new clip. Note how the clip on
top has been bent to a smaller size compared to the one underneath. This damage to the clip
reduces the force it can apply to its housing and makes it easier to dislodge. Specially modified
circlip pliers such as those shown in Figure 21 may be used to prevent damaging clips.
As the clip is fitted, listen for the crisp “snapping” sound that indicates it has dropped fully into place.
Orient the clip as shown in Figure 132: the opening in the clip faces along the axis of the barrel.
Ensure that both ends of the clip are positioned in full-depth sections of the groove
Always give the installed clip a close inspection after installation. Use the circlip pliers or a small
screwdriver or pick to check that it is tightly in place – as shown in Figure 132, apply an “opening”
load to the eyes to expand the clip. The clip should not move and should not spin in the piston. If
the clip moves, discard it and fit a replacement.
Figure 131 – The Two Sides of Circlips
Test load directions
Figure 132 – Clip Installation Detail
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Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Figure 133 – Over-Compressed and New Clips
WARNING
Clips that are loose will rotate in service and wear the piston circlip groove away resulting in a
loose fit and, eventually, the gudgeon pin being liberated & engine failure.
Circlips must be fitted and inspected correctly or engine failure will result.
 Fit the circlip on the propeller flange side of the pistons now – the second circlip will be fitted on
assembly to the connecting rod.
 Oil the pistons and cylinders using engine oil.
 One at a time, fit the compression rings (the first and second ring of each piston) into their cylinder.
Use a piston to press the rings down into the bore – this will position the rings properly perpendicular to
the bore, making sure they are not at an angle. Using a feeler gauge, measure the ring gap of each
ring and record the value in the build sheet. Ensure the gaps are within the limits given in Table 12.
0.50 – 0.60mm is typical in a 97.60mm bore though the gap will vary depending on the exact size of the
barrel. Figure 134 shows this process. The end gap can be adjusted if required, however this is a
standard engine-building process and will not be described here. Care must be taken to ensure that
pistons, rings and cylinders are maintained in sets so that the engine is eventually assembled using
parts which have been measured together – not with the rings which were checked in cylinder #2 being
fitted to cylinder #4.
Fitting rings to barrel
Measuring Ring Gap
Figure 134 – Checking Piston Ring Gap
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JEM0001-8
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
“Cut Out” Ring #2
“Square” ring #1
Figure 135 – Compression Ring Cross Section

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
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

Fit the rings to the piston.
The “square” compression ring goes into the groove closest to the piston crown. The compression ring
with the cut-out section fits in the next groove down (see Figure 135).
Some compression rings are marked with a dot or an “R”. Compression rings with either of these
markings must be fitted with the marking pointing towards the piston crown.
Check the fit of the compression rings to the piston. Ensure ring sliding clearance is within the limits
given in Table 12.
Note that the oil rings must be fitted so that the scraper ring ends (i.e. the join in the upper scraper ring
is not in line with the join in the lower scraper ring) are separated and the expander has not overlapped
itself.
Fit the gudgeon pin to the piston on the side where the circlip has not been fitted.
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JEM0001-8
7.3.2

Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Cylinders
Each cylinder should be clearly marked with a number using permanent marker or similar – these
numbers can be cleaned off at the end of the build using tool cleaner or similar. In the meantime the
numbers will allow the overhauler to easily identify cylinder head / piston / rod / cylinder sets. The
numbering system of the cylinders for the engines is given in Figure 3.
Optional tip: Apply temporary
mark (using a marker pen or
similar) to the underside of the
cylinder flange, in line with the
thrust marker on the piston.
Note fin cut-outs – these
face the sump when fitted
Figure 136 – Piston / Ring / Cylinder Assembly
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
If new cylinder heads are being used in the build then lapping the cylinder to the head is not required.
Otherwise the procedure noted in Section 7.3.4 must be followed.
Fit the rings to the piston. Orient the ring gaps at 120° intervals around the piston so that it is unlikely
that the gaps will ever line up. The rings must also be oiled for assembly.
Fit the piston to the cylinder (using a commercial ring compressor or a special tool per Figure 18) from
the underside (skirt side) of the cylinder. Do not push the piston far up into the cylinder as this makes
assembly difficult – it should be left as shown, down near the cylinder skirt.
Ensure the piston is oriented correctly into the cylinder – the side of the cylinder with the cut-out areas
in the fins faces the engine sump. Piston orientation is noted in Section 7.3.1. A good tip here is to
apply a temporary mark to the underside of the cylinder showing the front side, making later assembly
easier.
Start the gudgeon pin into the piston as shown in Figure 136 (left).
Fit the cylinder base O rings to the cylinder.
WARNING
Ensure that the thrust direction markings of the pistons are oriented correctly
Ensure that the cylinders are oriented correctly (top/bottom).
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JEM0001-8
7.3.3




Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Through-Bolt Nuts
Count out a set of engine through-bolt nuts.
12-point nuts with washers must be used on all cylinder base applications.
Check that all nuts and washers are clear of the radius on the base of the cylinder barrel. Figure 137
(right) shows how using certain (large-flange) nuts can result in the nut hitting on the radius at the
cylinder base. To avoid this it is necessary to use a “Small-flange” nut per Figure 137 left, or a nut
which has been modified – the diameter of the nut base can be reduced in a lathe. This requirement
also applies to the washers used: these parts are custom made for Jabiru from hardened steel –
substitutes must not be used.
Later engines (See Section 13 for serial number ranges) use 7/16” hardware on the engine through
bolts and studs. On these parts a custom-made nut (shown in Figure 138) is used. At overhaul these
are to be removed and 7/16” 12-point nuts & washers fitted (Figure 138 right).
Nut on assembled engine. Note “new type”
barrel, small-flange 12-point nut & washer
shown.
Figure 137 – Through Bolt Nut Installation Detail
3/8” MS21042style nut
3/8” 12-Point nut
7/16” nut, custom stainless
7/16” nut, 12-Point (& washer)
Figure 138 – 12-Point Nuts, 7/16” Hardware (on right)
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Engine Overhaul Manual
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Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
WARNING
MS21042-type nuts must be replaced with 12-point nuts at overhaul or whenever the barrel is
removed for maintenance.
Assembly with nut hitting barrel radius can lead to engine failure
7.3.4


Cylinder heads
Each cylinder head should be clearly marked with a number using permanent marker or similar – these
numbers can be cleaned off at the end of the build using tool cleaner spray. In the meantime the
numbers will allow the overhauler to easily identify cylinder head / piston / rod / cylinder sets. The
numbering system of the cylinders for the engines is given in Figure 3.
Note that the 2200 engine uses two different cylinder heads – one for cylinders 1 & 4 and another for 2
and 3 - Figure 139 refers. The Jabiru 3300 engine uses the same cylinder head for all cylinders –
though they are fitted with different induction or exhaust pipes depending on where they are fitted to the
engine.
Figure 139 – Cylinder Head Comparison (2200 head on left, 3300 on right).



Where second-hand heads are used they will have had their valve seals tested as detailed in Section
5.11.5. This process also applies when fitting new cylinder heads: the seal of each valve must be
tested as detailed in Section 5.11.5. If the seal is not good enough then the valve and seat will need to
be lightly cut. After cutting ensure that the cylinder head and valves are thoroughly washed to remove
all residue of the valve cutting paste.
Where new valve springs are used, inspect both ends for sharp edges and burrs which may damage
the valve spring washers. Polish off any edges or burrs found.
Prior to installing valves into the head, check the collet grooves are clean and free of metal burrs. Also
check the grooves in the collets themselves. Test fit each pair of collets onto the valve stem retaining
them in place with a Top valve spring retaining washer, check the valve rotates smoothly between the
collets. DO NOT install if there is excessive friction (this can can failure of the Top spring retaining
washer) another set of collets should be used.
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Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Using a hand press to
install new rocker bushes
Detail (solid lifter
type rocker shown)
Fitting valve & spring
Figure 140 – Fitting Valves to Head, Fitting Bushes to Rockers

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
Fit new O rings (2) to the rocker shaft bore of the cylinder head and 2 new O rings to the pushrod tube
bores. Use Nulon L90 to lubricate the O rings for assembly and to prevent damaging them while fitting
the rocker shaft and pushrod tubes. Do not use rubber grease as it will attack these O rings and metal
parts. Note that the large rocker cover O ring is fitted later in the assembly process.
Lubricate the valves and valve guides using oil, then fit the valve springs and collets to the cylinder
head using a spring compressor as shown in Figure 140. Ensure that the lower steel washer (shown at
the lower left of Figure 92 – left) is fitted to the base of each spring.
Note that the rocker shaft and valve rockers are fitted later in the assembly process. However now is
the time to fit new bushes to the rocker arms (if needed). A special tool and a hand press (as shown in
Figure 140) simplifies this job. Orient the new bushes so that the joint in the bush is pointing away from
the crankshaft. Additional details are shown in section 5.11.8.
Fit the induction pipe to the head, again taking care that the correct pipe is fitted to the correct head (the
pipes are stamped with their cylinder number). New gaskets must be used.
If new heads are being fitted to an engine then in most cases some small Welch plugs must be fitted to
the head. For engines using the external oil feed tube for the rocker gear small tubes must also be
fitted to the head. Both of these parts are pressed into the cylinder head (Figure 141).
For engines using the hollow pushrod oil feed the oil ports in the side of the heads are not used. In that
case 2 Welch plugs (Figure 141, right) are fitted to the head – one on each side – to blank them off.
Fit the outer pushrod cover retaining circlips to the heads as shown in Figure 180. Note the orientation
of these clips: the opening of the clips must point towards the access hole (and 1/8” NPT plug) for the
lower head bolt. In other orientations the clips may interfere with the fit and function of the pushrods.
Lube tube ready to be pressed into head
Welch plug ready to be pressed into head
Figure 141 – Cylinder Head Welch Plug & Lube Tube Installation.
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7.4




Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Subassembly D – Sump
It is acceptable to fit the induction plenum chamber to the sump before fitting the sump to the engine.
However for this manual the sump will be fitted first and the plenum later.
If the crankcases have been surfaced and line-bored it is possible that the sump dowel pins may not
align correctly. After the crankcases have been joined the sump must be dry-fitted to confirm that
everything lines up as it should. In some cases some of the mounting holes through the sump may
have to be enlarged slightly using a small round file and the locating pins may not fit. This is unusual
and generally should not occur, provided that the cases have not been surfaced by more than the
maximum allowable amount. Check for alignment of all mounting screws and for the fit of the sump
against the gear case at the rear of the engine.
After dry fitting, ensure that all dowels are in place (if applicable – early engines had none).
Fit a new O ring to the oil filler housing and to the dipstick.
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JEM0001-8
7.5
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Subassembly E – Flywheel, Ignition Coils, Starter Motor And Alternator
7.5.1 Ignition Coils
 Ignition coils are fitted with insulating washers between the coil and the mounting post. These are
essential as they greatly reduce the operating temperature of the coil, improving its longevity.
 Ignition coils must be fitted with the output lead pointing in the direction of propeller rotation. Coils
installed backwards may fire with the wrong timing or not work at all.
Insulating washer between coil and mount
Figure 142 – Ignition Coil Insulating Washer, Alternator Stator Thickness
7.5.2 Alternator
 If a new alternator stator is being fitted it must be measured to ensure proper clearance (Figure 142,
right). Note that dome-head screws are used in the alternator magnet housing (Figure 143, right) are
used to allow clearance from the stator – if normal socket head screws are used here alternator
damage will result.
 Screw the alternator stator to the mount plate using machine screws. A small amount of Loctite 263 is
used on these screws.
7.5.3 Flywheel
 If the engine is being updated to a “Starfish” style flywheel then the alternator rotor and the ignition
magnets must be fitted – otherwise these parts are left undisturbed on the flywheel during overhaul.
 Fit the ring gear to the flywheel using 6 off 1/4 x 1/2 Grade 8 bolts to the torque value given in Table 9.
Note the two tags fitted to the ring gear which are used by the tacho to measure RPM.
 Whenever working with the rare-earth magnets used in Jabiru Engines, remember that shocks (like a
sharp tap with a hammer) and heat (such as from a heat gun when removing the flywheel screws) can
de-magnetise the magnets.
 Each magnet retainer is fitted using 4 off 1/2" 10-32 countersunk screws. The magnets themselves are
potted in Silastic 1080 to prevent them vibrating. Note that the magnets must be set with their north
poles facing outwards. After assembly the magnet assemblies must be tested as detailed in Section
Table 13. If necessary new magnets may need to be fitted.
 The alternator rotor assembly is located on the flywheel using 4 roll pins. These are fitted to the
flywheel, then the rotor tapped into place using a soft hammer. The rotor is then screwed to the
flywheel using 4 off 5/8” x 10-24 button head cap screws. A small amount of Loctite 620 is applied to
these screws.
 Finally the “starfish” adaptor itself is screwed to the flywheel using 8 off 1/4" x 5/8" UNF cap screws &
Belleville washers (torque per Table 9). Loctite 620 is applied to these screws. Note that the “starfish”
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Jabiru Aircraft Pty Ltd
JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
has a front and a back – care must be taken to orient it correctly to the flywheel body, aligning the
datum holes in the starfish and flywheel body.
Locating roll pin
Flywheel tacho tag
Dowel hole
Datum hole
Timing mark
Figure 143 – Flywheel Assembly
7.5.4



Starter Motor
Assemble motor and starter housing, and include the earth wire, (refer to JSL 005-1 service bulletin for
details if the earth wire connection was not connected to the long through bolt on the starter motor).
Assemble bolts with a small amount of Loctite 243 on the threads of the long AN3 bolts and tighten,
check that the armature is able to rotate freely after tightening bolts.
Apply grease to the clutch gear and assemble into the starter housing, then fit the clutch housing.
The assembly is now ready to be fitted to the engine rear plate with the 3 socket head screws and
Belleville washers, torque per Table 9.
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7.6
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Subassembly F – Gear case and distributors
7.6.1 Engine Mount Plate & Tacho Pickup
 Note that the 2200 mount plate is different from the 3300 version – these parts cannot be interchanged.
As discussed in Section 5.13.4, for each engine there are 2 different engine mount plates available –
one to suit the 99 tooth ring gear and another to suit the 101 tooth ring gear. It is not mandatory for
these parts to be updated on overhaul, however the parts must be matched (ring gear to engine mount
plate) for proper operation.
 Fit the oil feed tubes (2 – 1 one for each distributor shaft) as shown.
 The tacho pickup post (where equipped) and the gearbox locating pins can also be fitted now.
 Where the hall-effect type tacho sender is used (Figure 145) it must be installed during final assembly
Tacho post with sender installed
Oil feed tube installed in back plate.
Orient with slot pointed upwards
Figure 144 – Installation of Oil Feed Tubes & Tacho Pickup Post
Figure 145 – Hall affect Tacho Sender
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JEM0001-8
7.6.2
Jabiru 2200 & 3300 Aircraft Engines
Distributor Case & Distributor Mounts
Figure 146 – Installation of Seals & Assembly

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


Fresh seals must be fitted to the case and to the distributor mounts as shown in Figure 146. Note that
later engines use a larger crankshaft timing gear and a thinner oil seal to suit. Oil seal size must be
matched to fit the gear used.
These seals must be well lubricated using grease for assembly – this part of the engine tends to run
slightly dry and generous lubrication now will greatly reduce wear of these parts.
The distributor posts, shafts and mount plates can be fitted to the distributor case now. Loctite 515
sealant is used on all mating surfaces.
Glue the distributor rotors to the shafts using 5-minute Araldite mixed with a suitable filler (such as
cotton flock) as shown in Figure 147.
New bushes must be fitted to the distributor housings as shown in Figure 147. Distributor posts must
be generously lubricated with Nulon L90 or grease.
If the distributor shaft has been replaced it will be necessary to rivet the drive gear to the new shaft as
shown in Figure 148. 3/16” stainless steel (Monel) blind rivets must be used. Ensure that the heads of
the rivet do not get caught on the edge of the shaft and that the tails are not so long that they project
past the shoulder of the shaft. Also ensure that the remainder of the rivet tails are driven out of the rivet
– otherwise they can work loose in service and damage the engine.
Figure 147 – New Distributor Shaft Bush Fitted – nopic x 1
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Jabiru 2200 & 3300 Aircraft Engines
Rivet – note that tail has not
yet been driven out of this one.
Rivets – tails have been driven out.
Figure 148 – Assembling Distributor Gear to shaft
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Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Subassembly G – Fuel Pump And Carburettor
7.7
7.7.1 Carburettor
 Pre-fit the carburettor to the rubber mount, ready to be fitted to the engine.
7.7.2




Fuel Pump
At a full overhaul a new fuel pump and new fuel lines are fitted.
Pre-lube the pushrod using a small amount of grease.
New gaskets must be used when re-fitting the pump. All joints must have 1 face coated with Loctite
515 sealant.
Apply Loctite 243 to the 5/16 x 1 1/4” cap screws and tighten as detailed in Table 9.
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JEM0001-8
Subassembly H – Final assembly
7.8


Now that each Subassembly is ready the overhauled engine can be final assembled.
Note that the entire crankcase assembly process including the fitting of pistons and cylinders MUST be
completed in one continuous operation otherwise the Loctite 515 Sealant around the crankcase join can
dry before uniform pressure is applied to the crankcase join by the cylinder nuts, so make sure that you
have all parts ready for completion up to this stage (i.e. pistons and cylinders) before starting to fit the
crankcase halves to the crankshaft.
7.8.1


Jabiru 2200 & 3300 Aircraft Engines
Crankcase Joining
During the joining process various sealants will be used which will cure quickly – therefore it is essential
that the overhauler be thoroughly organised before starting this task and that they work efficiently and
quickly once they have begun. If too much time is taken the engine must be disassembled and recleaned, ready for another attempt at joining.
Pre-Joining Checklist:
1. Ensure all tools, parts, sealants and compounds are available for the build and ready to be fitted.
Parts in particular must have been cleaned, inspected and had any necessary remedial work carried
out before beginning the final assembly.
2. Oil all bearings lightly.
3. Oil or grease (lightly) camshaft tunnel
4. Thrust bearings are installed correctly and oiled.
5. All required measurements have been taken – cam end float, crank end float etc.
6. For solid lifter engines, ensure the valve lifters are fitted and lubricated.
7. Count all engine through bolts and place them close to hand.
8. Count all engine through bolt nuts, confirm they have been chamfered (per Section 7.3.2) and place
close to hand.
9. Confirm that all gudgeon pins are started into their pistons & are ready to go.
10. Count all piston circlips and place close to hand.
11. Check that suitable spanners are available – torque wrench, special spanners for tightening the lock
nuts on the through-bolts, “crowsfoot” adaptors etc.
12. Confirm the orientation of the cylinders and the pistons within the cylinders.
13. Confirm that the sump oil pickup and strainer, through bolt dowels and studs have been fitted to the
crankcase.
14. Confirm that the cam is assembled to its gears, ready to fit.
15. Apply a little grease to the cam and to the lifters.
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Jabiru 2200 & 3300 Aircraft Engines
Sealant on case, note oil gallery is clear
Figure 149 – Applying Sealant to Case, Fitting to Crank
Figure 150 – Fitting The Second Case Half
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Jabiru 2200 & 3300 Aircraft Engines
Figure 151 – Tightening The Front Crankcase Studs




Apply a light coating of Loctite 515 sealant to one crankcase joining face. Ensure that all oil galleries
and feeds are free – an excess of sealant can block these, leading to engine damage.
Fit one side of the crankcase to the crankshaft, taking care not to dislodge any of the bearing shells or
mark them with a sharp corner.
Place the camshaft in the journals of the fitted case half.
Fit the second side of the crankcase. The front and rear studs must now have nuts fitted and tightened
lightly.
Figure 152 – Applying Sealant and O-Ring to Cylinder Base
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Jabiru 2200 & 3300 Aircraft Engines
Figure 153 – Fitting Gudgeon Pin
Figure 154 – Fitting Cylinder, Inserting & Tightening Through-Bolts
Figure 155 – Piston Orientation
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Jabiru 2200 & 3300 Aircraft Engines
Figure 156 – Torque Seal Applied




Apply a small amount of Loctite 518 sealant to the cylinder base and the cylinder base O ring (Figure
152). Wipe excess sealant off the base face of the cylinder before fitting. Then offer the cylinder /
piston assembly up to the engine. Double-check the thrust direction of the piston now – if necessary
rotate the piston in the bore to correct the orientation (Arrows / moulded lugs on propeller flange side of
the connecting rod). Insert the gudgeon pin and circlip, then fit the cylinder up against the crankcase.
Verify that the piston orientation is as shown in Figure 155: valve relief on the lower (sump side) of the
piston.
The orientation of the cylinder must also be double-checked – make sure the cut-outs in the fins are
facing the sump – these are to give clearance to the pushrod tubes. Figure 136 shows the cut-outs.
Fit the through-bolts to the engine. Care must be taken to centre the through-bolts so that the
same amount of thread shows on both sides of the engine. Refer to Table 6 for approved
configurations to be used at overhaul or maintenance. Note that the front studs of the engine use a nut
/ washer combination different to the other studs.
Tighten all through-bolts and studs to 20lb.ft without locking compound.
Table 6 – Hardware Configuration Summary
Size
3/8”
7/16”
-



Hardware Type
3/8” 12-point nut: reduced flange on cylinder
bases.
3/8” 12-point nut: full flange on front studs.
7/16” 12-point nut: reduced flange on cylinder
bases
7/16” 12-point nut: full flange on front studs
-
Washers Used
AN960-6 on front crankcase studs.
5/8” OD Hardened on cylinder
bases.
AN960-7 on front crankcase studs.
5/8” OD Hardened on cylinder
bases.
Loctite
None.
None.
Starting from the middle cylinders:
- Remove both nuts from one through-bolt
- Visually inspect the cylinder base for marks where the base of the nut has pressed against the lower
radius of the barrel.
- Tighten all through bolts and studs to the value given in Table 9. Ensure even amounts of thread
are visible on both sides of the engine for through bolts. Apply torque wrench to nuts on both ends
of through-bolts.
- Repeat for all through bolts and studs on the engine.
Mark the completed nuts with anti-tamper paint as shown in Figure 156. Note the torque seal applied to
the nut base / washer / cylinder flange to show if there is any movement in this location.
A special tool is available from Snap-On which speeds up the installation of the cylinder barrels – P/No.
FU14B is a small universal joint with a built-in 7/16” nut socket. This allows tensioning of the throughbolts without a crowsfoot – eliminating the need to make an allowance for the crowsfoot arm on the
torque setting. FU16B is the equivalent tool with a ½” socket for use on 7/16” 12-point nuts.
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Jabiru 2200 & 3300 Aircraft Engines
Figure 157 – Universal Joint tool FU14B (FU16B for ½” Socket)



Repeat this process on all the remaining through-bolts and studs.
Rotate the crank inside the crankcase. Assess the force required to turn crank: excess friction indicates
that bearings have tightened up and minimum clearances have not been maintained. This may indicate
an error in measurements or – in the case of a top-end overhaul – fretting damage to the cases.
Contact Jabiru Aircraft or our local representative for guidance. Assessing friction is an exercise in
judgement and overhaulers must develop a feel for this aspect. The engine being worked on may be
compared with another engine where practical.
Issue 1 of Service Bulletin JSB 031 noted that in some special cases where 12-point nuts are fitted to
older through-bolts the nut may overhang the thread of the bolts. This was due to the extra length the
12-point nuts. While this was acceptable in some cases for engines subject to the Service Bulletin
Issue 1 re-work it is NOT ACCEPTABLE during a normal engine overhaul. New design through-bolts
must be used which are long enough to accommodate the 12-point nuts.
WARNING

DO NOT EXCEED SPECIFIED TORQUE – through-bolt damage will result.
ALL BOLT TORQUE SETTINGS IN THIS MANUAL ARE “DRY” UNLESS STATED OTHERWISE
Correct tightening procedures must be used. See Section 3.8.3.
Fitting cylinders & through-bolts is a critical operation & must only be attempted by trained
technicians.
Excess sealant can now be wiped off the cylinder bases and the crankcase join – this is most easily
done once the sealants have dried.
7.8.1.1





Technicians reading this must understand the difference between “bolt tension” and “nut torque”.
Torque is the setting on the torque wrench & defines how much rotational force it takes to turn the nut.
Bolt tension is the actual tensile load in the bolt – the force holding the parts together.
Tuning a guitar is a good illustration of the difference between bolt tension and nut torque – for a given
torque on the guitar string adjustor the tone of the string might be too high or too low – in that case the
musician can set the string tension directly by turning the adjuster until the string tone is right. For a
through-bolt we cannot measure the tension directly and we are forced to make assumptions of the
relationship between nut torque and bolt tension – in effect we are trying to set the guitar string tone
indirectly by assuming that a given torque on the string adjuster will give a certain string tone.
Testing has shown that assembling these parts dry gives good, repeatable results for bolt tension.
Altering these parameters has unpredictable effects and is not recommended.
7.8.2


Additional Information – Through-Bolt Tension
Option – Fitting Oil Pump
It is possible to fit the oil pump now rather than later. This allows the overhauler to turn the cam by
hand as the oil pump housing is being tightened to check for binding between the oil pump gears.
Full fitting details are given in Section 7.8.17.
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7.8.3
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Setting Cam Timing
Wire indicator adjusted to TDC
Dial gauge mount plate
Figure 158 – Measuring Top Dead Centre







In newer engines the datum marks on the gears are invariably accurate, however timing must still be
checked in case older parts are being used.
Fit a mount plate and dial gauge to cylinder #1 of the engine and use the dial gauge to accurately locate
top dead centre for that cylinder. This is done by using the dial gauge to estimate TDC then bending
the wire to point at 0° on the degree wheel. Then rotate the engine to the right (against rotation) until
the dial gauge records movement of 0.5mm from TDC and record the degree wheel reading. Move the
engine back to 0° then turn it to the left until the gauge reads 0.5mm – record the degree wheel reading.
Calculate the centre point between these two readings – this is the true TDC for this cylinder. The
engine can then be rotated until the wire points at this reading and the wire re-bent to point at 0°. Care
must be taken from now on not to bend the wire! Double-check this position by repeating the above
procedure – twisting to the left, then to the right.
Rotate the cam until the two timing marks on the large cam gear are pointing towards the crankshaft.
The camshaft drive gear can now be fitted to the end of the crank as shown in Figure 159 – so that the
tooth on the crankshaft gear with the timing mark is between the two teeth of the cam gear with timing
marks.
A single cap screw can now be added to the crankshaft gear to lock it in place relative to the crankshaft.
Once this is done the timing must be checked by reading directly from the camshaft.
For a hydraulic lifter engine – for measurement purposes – fit a hydraulic lifter to the lowermost port of
the engine (as shown in Figure 160 – alternatively a special tool such as that shown in Figure 29 can be
used).
Now rotate the engine to find the point of maximum lift of the cam lobe being checked. The procedure
here is the same as for finding TDC for the cylinder – with the exception that the timing pointer wire
must not be bent! Estimate the point of max lift for the cam, then turn the engine either way until the
dial gauge records 0.5mm movement. Record the timing readings and calculate the centre point.
Peak lift occurs about 70 – 72° after Bottom Dead Centre (71° typical) for the exhaust lobe and 68 – 72°
(71° typical) before Bottom Dead Centre for the intake lobe.
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Jabiru 2200 & 3300 Aircraft Engines
Datum hole aligned with timing marks on gears.
Timing marks on crank gear and cam
gear aligned correctly, cap screw fitted
locking crank gear to crank.
Figure 159 – Setting Cam Timing
Using dial gauge to find peak lift of cam lobe
Extremes of engine rotation for 0.5mm
drop on dial gauge – peak lift is halfway
between these points
Figure 160 – Checking Cam Timing #1
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Jabiru 2200 & 3300 Aircraft Engines
Peak lift found at 70°-71°
from Bottom Dead Centre
Figure 161 – Checking Cam Timing #2
7.8.4







Sump
As an alternative to the order given below the sump may be fitted after the engine backing plate.
Lightly apply Loctite 515 to the horizontal mating face of the sump. Note that our experience is that it is
easier to apply the sealant to the sump than to the crankcase.
Fit the sump using cap screws and locating pins as shown in Figure 162. Note that on early engines
the length of the screw which is in line with the internal oil pickup is 5/8” long compared to ¾” for all
other locations. Later sumps have a raised boss for this position allowing the longer screw to be used.
Some engines have provision for a pair of cap screws to secure the rear of the sump to the engine
mount plate (see Figure 49). These screws have proven unnecessary and should be omitted during
overhaul.
Attach the oil filler mount fitting to the right crankcase using Loctite 243.
Fit the oil filler tube to the engine, lubricating the tip with Nulon L90 for assembly. Tighten the grub
screw which holds the tube in place.
The dipstick can now be fitted.
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Jabiru 2200 & 3300 Aircraft Engines
Figure 162 – Fitting Sump
Oil filler tube fitted.
Tighten grubscrew here
Figure 163 – Oil Filler Tube Installation
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7.8.5
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Engine Mount Plate
Figure 164 – Sealing Engine Mount Plate
Figure 165 – Fitting Engine Mount Plate
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



Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Apply Loctite 515 sealant to the
rear of the crankcase and sump as
shown in Figure 164. The cam
drive gears should also be
lubricated with oil now, before the
gear cover is fitted.
Tighten the screws holding the
plate to the crankcases. Note that
different sized screws are used on
the plate - Figure 166 refers.
= 5/16 x 1 1/4" UNC
1 x Belleville + 1 flat washer (2)
= 1/4 x 5/8” UNC (2)
= 1/4 x 1” UNC (4)
= Not Used
Note that some engines were
equipped with 2 extra screws into
the sump. These are unnecessary
and should be omitted at overhaul.
Loctite 243 is applied to the holes
for the gearbox mounting screws.
Figure 166 – Engine Mount Plate Screw Locations
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7.8.6
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Distributor drives
Figure 167 – Fitting Distributor Case & Setting Timing






Ensure distributor shafts are generously lubricated before assembly.
Apply Loctite 515 sealant to the gear case as shown in Figure 167.
Rotate the engine to 25° before TDC on the compression stroke (indicated by the cam and crankshaft
timing marks lining up) as shown in Figure 167.
Both distributor rotors must point to the timing mark engraved on the distributor mount plate – use a
ruler to check that they are nearly parallel as shown in Figure 168. They will not be exactly parallel but
they should be close – and provided the timing mark lines up with the tip of the cap it will work properly.
The gear case can now be tightened onto the engine mount plate to the torque specified in Table 9.
Note that certain 3300 engines (See Section 13 for serial number information) have different flywheel
starfish. These parts have been indexed to give 20° or 23° BTDC for spark timing instead of the original
25°. These are engraved with “20° BTDC” or “23° BTDC” as appropriate. When using this part the
timing procedure given herein must be adjusted to suit.
Rotor timing mark
Figure 168 – Setting Distributors, Checking Rotor Position
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Jabiru 2200 & 3300 Aircraft Engines
Figure 169 – Checking Rotors, Tightening Distributor Case


Tighten the screws holding the
gearbox to the engine. Note that
different sized screws are used on
the plate - Figure 170 refers.
= 1/4 x 3/4" UNC
+ 1 x Belleville washer (3)
= 1/4 x 1 1/4” UNC (6)
= 1/4 x 1 3/4” UNC (4)
+ Belleville washer
Note that early engines used 1/4 x 1
1/2” screws in place of 1/4 x 1 3/4”.
Overhaulers must check the thread
depth before final fitment of these
screws.
Figure 170 – Gearbox Installation
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7.8.7







Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Flywheel and Alternator Rotor
While the engine is still set at 25° before TDC (or as required to set the distributor timing) the flywheel
will fit onto the engine with its magnets aligned at the ignition pole positions. For the 2200 engine this
means the magnets are pointing to the left and right of the engine. For the 3300 the magnets are at the
1 o’clock, 5 o’clock and 9 o’clock positions. There is also a timing mark (a hole) drilled in the starfish (or
flywheel for non-starfish engines) which aligns to a corresponding hole in the crankshaft gear. Figure
172 refers.
Note that fitting dowels of some form or another is a mandatory update – older engines which were not
originally equipped with dowels must be upgraded at overhaul.
Remove the temporary cap screw which was used to lock the gear to the crankshaft & preserve the
cam timing.
Ensure that the crankshaft screw threads are clean of locking compound by running a bottoming tap
through each of them. The tap should be run carefully by hand to ensure the threads are not damaged.
The tap used is either a 3/8-UNF or 5/16-UNF depending on the configuration.
Once the timing marks are aligned and the temporary locking screw is removed, the flywheel can be
fitted to the engine.
Align the timing marks and then tap the dowels through the flywheel into the crank using a soft hammer.
The 6mm dowel pins (3 off) are fitted with a small amount of Loctite 620. Note that 20mm or 25mm
long dowels are required, depending on the configuration of the engine. The dowel holes in the
crankshaft are drilled to depth so the dowels are tapped in until they stop. After installation measure
how much dowel protrudes from the crank: approximately 18mm is required for non-starfish engines
and 12mm for starfish types. Excess length must be corrected as it will cause assembly problems.
Starfish engines use 5/16 x 1” or 3/8” x 1” screws, others 5/16 x 1 1/4”. All types must be fitted using
Loctite 620 and have a Belleville washer fitted. Apply a match-tip sized portion of Loctite to the threads
in the crankshaft and the same sized amount to the threads of the screws. Rub the threads of the
screws against each other to distribute the Loctite reasonably evenly over the first 3 threads. The
screws can now be fitted. Torque them to the value specified in Table 9 – using a normal diagonal
pattern. Figure 173 refers. Work fast – remember Loctite 620 can cure very quickly, especially when
cure accelerator spray (Loctite 7471) is used.
NOTE:
The crankshaft and flywheel mating faces must be kept dry and clean during installation
Figure 171 – Applying Loctite, Fitting Dowels.
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Jabiru 2200 & 3300 Aircraft Engines
Figure 172 – Flywheel & Crank Timing Marks
Figure 173 – Fitting & Tightening Flywheel Cap Screws
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7.8.8
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Ignition Posts & Alternator Stator
Alternator mount post bolts
Coil mount screw
Figure 174 – Ignition Post & Alternator Stator Installation




The alternator and ignition coil posts are held to the engine using 4 off AN4-37A bolts. Ensure that
metal-lock nuts are used as shown in Figure 174. Roll pins are also used to hold these parts in position
– tap them together on assembly using a soft hammer.
Once the posts are in place the ignition coils can be fitted. The simplest method is to use a large 0.010”
feeler gauge – lie this gauge against one of the magnet poles of the flywheel – the magnetism will keep
it in place. Then rotate the engine until this pole lies beside the coil whose gap you wish to set. Again,
the magnetism will hold the coil against the feeler gauge and the coil mounting screws can now be
tightened. Once both coils have been positioned this way check the gap between each magnet pole
and each ignition coil – on older engines the magnet poles may not be in exactly the same position on
the flywheel which may vary the gap. In this case a compromise adjustment must be found to get all
coil gaps within the limits set in Table 12.
Note that insulating washers are fitted between the ignition coils and the mounting post – this is to
minimise heat transfer into the coil.
When installing the coils note the orientation – in all cases the output lead from the coil must point in the
direction of propeller rotation.
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7.8.9
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Distributor Caps
Distributor cap fitted
Figure 175 – Distributor Cap Installation

Fit the distributor cap to the mount plate using the clamps & cap screws. Note that the cap must fit
tightly – if there is any movement in the cap once the clamps have been tightened then a new cap may
be required. In early engines these clamps tended to be slightly too long so clamps may be modified –
inspection of the cap will show if it has worn or if the clamps are the wrong length.
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Jabiru 2200 & 3300 Aircraft Engines
7.8.10 Cylinder Heads


The cylinder heads must be fitted to the engine in a sequence as the rocker shafts are installed in-situ.
The recommended sequence is: fit an upper head – say 5 or 6 for a 3300 engine – first, then work
downwards, completing each head assembly in turn.
For each head the following sequence must be followed:
1. The outer bottom circumference edge of the hydraulic lifter should be lightly polished to remove any
burrs or sharp edges.
2. For hydraulic lifter engines, fill the lifters with oil (using an oil can - Figure 176) and fit the lifters to
the crankcase. The outside of the lifter must also be well lubricated with oil before fitting and note
also the light covering of grease which has been applied to the camshaft lobes – this is to minimise
wear during initial start-up. Note that solid lifter engines have their lifters fitted before crankcase
assembly – there is no way to do it once the case halves are assembled.
3. For engines equipped with roller cam followers the follower locking plates must be installed now –
see Figure 177. This plate should be a neat fit with a small amount of clearance from the lifter. It
may be necessary to lightly linish the plates before installing to remove sharp edges etc. Note the
orientation of the plate when installed: the two “legs” on the plate must point out of the case.
4. Fit new O rings to the crankcase to seal the pushrod tubes (solid lifter models) – see Figure 176.
5. For hydraulic lifter engines, fit new O rings to the pushrod tube adaptors. Again these must be well
lubricated with oil or Nulon L90. Fit the adaptors to the crankcase.
6. For roller follower models, the oil return manifolds can be fitted now. Fit new O rings and use a
small amount of Loctite 515 to seal the manifold to the engine. Figure 178 shows the manifolds
installed.
7. Fit the pushrod tubes (2) to the crankcase.
8. If the engine uses an external oil feed pipe this must be fitted between the cylinders. It should be
fitted but the clamps not tightened until all the heads are fitted. For later specification engines which
use the pushrod tubes to feed oil to the rocker gear this step is omitted. Note that if an engine has
been converted from the external oil feed to the new hollow pushrod oil feed it will be necessary to
fit blanking plugs to the old oil feed holes in the sides of the crankcase as shown in Figure 183.
Solid lifter engines must use the external oil feed tube system.
9. Fit the cylinder head to the cylinder, feeding the pushrod tubes into the head – see Figure 180.
10. Apply high-temperature lubricant to the threads of the cylinder and the cylinder head screws – these
are susceptible to rust which can lead to inaccurate bolt tension readings later in service. The
lubricant is designed to prevent rust on the threads and to ensure a consistent torque setting during
the engine’s service life. Figure 179 refers.
11. Install the cylinder head bolts and washers with a light tension setting. In particular the lower head
screw (which is accessed via the hole inside the rocker cavity) must be left loose – the special
washer under this screw can rub against the rocker tubes and so must be carefully positioned to
avoid this. Figure 179 (right) shows this screw being tightened.
12. Using the spring compressor tool shown in Figure 10 and Figure 182, open both valves to allow the
installation of the valve rockers. This step may be bypassed for a solid lifter engine if the overhauler
prefers, but even for those engines this tool makes the assembly simpler by allowing the heads to
be fitted as complete assemblies.
13. Fit the valve rockers, taking care that the pushrod is correctly seated into the sockets in the lifter and
in the rocker. The rockers and the rocker shaft must be lubricated well with Nulon L90 or oil as
shown in Figure 181 and then driven in using a suitable punch and a soft hammer. The shaft is
punched in with the rounded end leading.
14. Fit the rocker shaft locking screw and remove the valve compressor tool.
15. Tighten the cylinder head screws (6) to 15 lb.ft and then to the value specified in Table 9 using a
standard diagonal tensioning pattern.
16. Fit the tapered blanking plug to the access hole for the lower cylinder head screw (shown in Figure
180 – left). Note that this plug must not be over-tightened. If the plug is done up too tightly then
over time its tapered thread will wear the thread in the cylinder head, requiring it to be screwed in
further and further to be tight. Eventually the thread can be worn so much that the tapered plug will
not lock in. A tension of about 6lb.ft is sufficient for this plug.
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Jabiru 2200 & 3300 Aircraft Engines
17. For engines using an external oil feed tube for the rocker gear the rubber “T” pipes can be centred
between each head and the clamps tightened now.
18. For a solid lifter engine, once all the heads are fitted the valve clearance can be adjusted.
O ring fitted
to crankcase
Figure 176 – Fitting Hydraulic Lifter To Crankcase
Roller follower
locking plate
Crankcase –
locking plate slot
Crankcase – locking plate
& roller follower (1) fitted
Figure 177 – Crankcase & Locking Plate
Figure 178 – Oil Return Manifold Fitted
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Jabiru 2200 & 3300 Aircraft Engines
Note induction pipe already fitted to head
Applying high temp thread lube
Tightening lower head screw
Figure 179 – Applying Thread Lubricant & Tightening Lower Head Screw
Cylinder marked with number
Note orientation of circlips
Access hole for lower head screw
Figure 180 – Fitting Rockers #1
Lubricated rockers ready to fit
Fitting rocker shaft
Figure 181 – Fitting Rockers #2
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Assembly complete.
Note
rocker shaft lock screw fitted.
Figure 182 – Fitting Rockers #3
Oil feed tube from crankcase
port to cylinder heads
Figure 183 – Rocker Lube (Left) & Crankcase Oil Port Blanking Plug

For a solid lifter engine, to adjust the valve clearances use the following procedure:
1. Start with the top valve in the top head. Rotate the engine on the work stand to the point where the
valve is fully depressed then rotate it through another whole revolution. This will place the follower
exactly on the “back” of the cam where there is no lift. Note that the engine should always be turned
in the direction of its normal rotation.
2. Using a spanner and screwdriver (or special tool as shown below) adjust the clearance to 0.010”.
3. Repeat this process for each valve in the engine.
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Jabiru 2200 & 3300 Aircraft Engines
Figure 184 – Valve Clearance Adjustment (Solid Lifter)
7.8.11 Induction Plenum & Tubes
Figure 185 – Induction Manifold Installation
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The upper induction pipes have all been fitted to the cylinder head during sub-assembly and by now it
will be obvious if any have been fitted to the wrong head.
Fit the diffuser(s) inside the plenum chamber halves. 2200 and most 3300 engines both use an “airfoil”
diffuser shaped as circled in Figure 185 (Left). Later 3300 engines use two round diffusers.
The two halves of the plenum chamber are fitted together as shown, using Loctite 515 sealant between
the halves.
Once assembled by hand the plenum chamber can be fitted to the engine.
Insert new O rings into the plenum chamber as shown. In this application the O rings must be installed
dry – sealant will be added later.
Fit the rubber joining hoses onto each induction pipe and push them up towards the head. The hose
clamps should also be fitted now, but not tightened.
One by one, fit the lower induction pipes into the plenum chamber. Before fitting, wipe the inside of the
socket of the plenum chamber with Loctite 2 gasket sealant, making sure that the O ring is coated.
Additional sealant is applied to each stub pipe. Care must be taken to get the amount of sealant right –
too little will result in leaks which can dangerously affect the fuel/air mixture while too little will form
blobs inside the induction manifold and need to be cleaned out.
While the sealant is still wet push the rubber joining hoses over the joints in the pipes. Mark or measure
the pipes so that the hose is centred over the join. Then tighten the hose clamps – orient the clamps for
easy access when installed on the aircraft.
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
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Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
The carburettor mount is sealed to the rear face of the plenum chamber using Loctite 515 and attached
using cap screws as shown in Figure 187. Apply Loctite 243 to these screws.
The carburettor coupling and carburettor can now be fitted as shown, making sure that the earth strap is
fitted between carburettor and plenum as shown. Do not use any lubricant on this connection as it can
result in the carburettor slipping out of the coupling and engine stoppage.
Figure 186 – Fitting Induction Pipes to Plenum Chamber
Carburettor mount screwed
to plenum chamber
Carburettor earth strap
Figure 187 – Fitting Carburettor
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7.8.12 Exhaust Pipes
Figure 188 – Exhaust Installation
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Early engines used gaskets between the cylinder head and the exhaust manifold which must be
renewed at overhaul or top end inspection. For engines in this configuration a shake-proof washer
must be fitted to the flange screws.
Newer engines use a metal-on-metal seal with a 45° seat at the exhaust port of the head – for these
engines there is no seal and no shake-proof washers needed.
Loosely fit the exhaust pipes to the engine. Each pipe will have 3 (for gasket type) or 2 (metal seat
type) cap screws holding the pipe to the head.
On the final assembly into the aircraft the muffler will be fitted and positioned, then the screws
tightened.
7.8.13 Carburettor
 Cap the air and fuel inlets before taking the engine out of the overhaul room.
7.8.14 High-Tension Leads & Spark Plugs
Figure 189 – Firing Order of Distributor Caps


Note that in Figure 189 all distributors are shown looking from the flywheel end of the engine. “Exhaust”
and “Intake” refer to the position of the spark plugs in the cylinder – on the exhaust or intake side of the
head.
Assemble the high-tension leads onto the engine, cable-tying them as shown in Figure 175.
WARNING
Do not use lubricant to fit the HT lead boots as this can result in the lead slipping out of the socket
in service.
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Jabiru 2200 & 3300 Aircraft Engines
During assembly, check each HT lead fitting for tightness in the distributor cap; expand each metal
fitting until it snaps neatly into place in the cap.
NGK D9EA spark plugs are used in Jabiru Engines. If other brands are used care must be taken to
ensure they are equivalent to the D9EA in all respects. Note that Resistor type plugs are not
recommended as they reduce the spark strength and can contribute to difficult starting – and that
Iridium plugs are generally resistor types.
The spark plug gap is set to the value given in Table 12. Generally around 0.23” works well though the
gap can be reduced to the minimum (0.018”–0.020”) during winter to give easier starting
Always use a high-temperature graphite lubricant such as anti-seize when fitting the plugs. Tighten the
plugs to the setting given in Table 9. Note that excess lubricant on the plug thread can cause plug
misfiring when heated.
HT leads fitted. Note how
leads are bundled and
restrained to prevent rubbing.
Figure 190 – HT Leads Fitted To Engine
REMOVE ENGINE FROM STAND.
7.8.15 Front Crankshaft Seal Housing
Figure 191 – Fitting Seal To Housing
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Jabiru 2200 & 3300 Aircraft Engines
Figure 192 – Front Seal Housing Ready To Fit

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
Note that this task must be performed before fitting the propeller drive flange or the oil pump housing.
Apply Loctite 515 to the inner face of the seal housing and fit the new seal as shown in Figure 191.
Using a hand press with dies made to suit makes this job much easier and is strongly recommended.
Fill the seal with high temperature grease or commercial seal lube and fit the housing to the engine as
shown in Figure 193 (right). Note the orientation of the housing. Use 4 off 5/16” cap screws with
Loctite 243 on the threads. Note that earlier engines used 1/4” screws. Either type assembly is
acceptable.
7.8.16 Propeller Flange
Figure 193 – Preparing To Fit Propeller Flange
WARNING
This task requires a second person. It is safety critical and should only be attempted by
experienced, competent overhaulers.



Before beginning this task ensure that all parts, hardware and compounds are close to hand and ready
to be fitted. Dry-fitting the flange before final fit-up is strongly recommended. In some cases some
paint may need to be removed from the front of the crankshaft or from the flange to allow the flange to
fit easily.
The cure time for the retaining compounds used in this task can be short and so this task must be
completed quickly and efficiently.
Before beginning the fit up, use taps to ensure that all threaded holes in the crankshaft have been
cleaned and the old retaining compound removed. This must be done carefully and by hand to make
sure the tap engages properly with the thread and does not damage it. Prop flange retaining screw
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Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
holes are 3/8” UNF while the rear flywheel retaining screw holes are 5/16” UNF or 3/8” UNF. After
removing the tap use compressed air to blow out any debris from inside the holes.
Dry fit the cap screws to the propeller flange and verify that there is sufficient thread engagement into
the crankshaft – a minimum 9mm (0.0.354”) of full thread engagement is required – which generally
equates to a total of around 11-12mm (0.433-0.472”) measured from the tip of the screw to the flange
mating face. If a Belleville (cone or spring washer) is used, the compressed thickness of the washer
must be accounted for – the numbers given here assume a std Jabiru Belleville washer is fitted (and
compressed) while measuring. While this is not normally an issue when using a Jabiru propeller flange,
manufacturing tolerances mean that this must still be checked. If using a non-Jabiru flange then this
dry fit stage is of critical importance to ensure that the flange is fitting properly (not binding on the crank,
is sitting co-axial with the crank etc). If replacement hardware is used ensure that it is “Unbrako 1960”
grade or equivalent.
Clean the threads of the screws using Loctite 7471 cure accelerator & allow to air dry. After priming,
ensure the threads stay clean – contamination with oil (even skin oils from fingers) can reduce the
strength of the bond of the retaining compound.
Clean the threads in the crankshaft using Loctite 7471 cure accelerator & air dry.
Ensure that there is no paint, Loctite or other contaminants on the internal face of the propeller flange
where the mounting screws and washers seat.
Because the retaining compound sets quickly it is recommended to pre-heat the propeller flange to
around 60 – 80°C using a heat gun or similar. At this temperature the flange expands and will fit over
the dowel pins more easily.
Fit the flange to the crankshaft; this can be done most quickly by carefully positioning the pre-heated
flange in place with the dowels lined up with the holes in the flange. Then, using a piece of timber as a
“soft” driver fitting inside the flange, drive the flange into position with a hammer.
Alternative method for flange installation:
- After initial cleaning of the threads of the crankshaft and of the cap screws fit the flange to the
crankshaft using 3 of the screws, tightening evenly to ensure flange is pulled correctly into position.
- Do Not Apply Loctite! Tighten to the torque specified in Table 9.
- Visually inspect the flange and ensure it is correctly fitted: ensure there is no gap between the
flange and the crank and that the flange is sitting straight.
- Remove screws; the flange will remain in place on the dowel pins.
- Repeat the steps given above for final cleaning and application of Loctite.
WARNING
It is vitally important that the screws are removed, male and female threads are cleaned and the
screws re-installed with Loctite: failure to apply retaining compound can result in engine failure.
 Once the flange is in place and both male and female threads are clean apply a small amount –
approximately the size of a large match head – of Loctite 620 retaining compound to the flange screws.
Roll the threads of two screws together to spread the compound evenly over the threads of both,
ensuring that the same amount adheres to both and is evenly spread.
Apply the same amount (approximately the size of a large match head) of Loctite 620 to the threads in the
crankshaft. Apply the compound as shown in Figure 193: Use a scribe or small probe to apply the Loctite to
the threads inside the crankshaft. Apply in the range 1 – 6mm from the front face of the crank.
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Jabiru 2200 & 3300 Aircraft Engines
Figure 194 - Installing the Propeller flange

Allow the retaining compound time to cure (refer to manufacturer specifications) before starting the
engine.
NOTE:
Ensure the propeller flange and crankshaft mating faces are clean and dry before installation
7.8.17 Oil pump
Outlet port O ring
Oil pump dimples
Figure 195 – Fitting Oil Pump & Port Plate
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Jabiru 2200 & 3300 Aircraft Engines
Figure 196 – Engine Turning Tool, Installed Oil Pump
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Fit a new BS112V O ring to the port plate to seal the pressure delivery port (Figure 195).
Apply Loctite 515 sealant to 1 face of each joint – as shown with the rear side of the pump housing and
the rear side of the port plate is recommended. Ensure the O rings are coated with sealant.
Fit the port plate to the engine, then fit the new woodruff key and the oil pump gears to the camshaft.
Ensure that the key is sitting correctly and that the dimples on the oil pump are both visible as shown in
Figure 195. Occasionally the key may need to be lightly sanded to fit the cam or pump gears. This can
be done by placing a piece of 600 grit wet and dry emery paper on a flat surface and rubbing the key
against it. The fit needs to be snug however – do not remove too much material.
Fit the outer pump housing over the gears and insert & hand tighten the retaining cap screws. Use
Loctite 243 on the threads and ensure the Jabiru bird is oriented correctly.
While the housing is still loosely held to the engine, rotate the crankshaft through at least 2 full
revolutions. This turns the cam and allows the oil pump to find its preferred position. The housing can
now be tightened to the value given in Table 9. Failure to turn the engine can result in the oil pump
being offset from the cam axis – this applies side loads to the cam and can eventually crack it or break
the tip off altogether.
7.8.18 Oil Pressure Relief Valve
Figure 197 – Lapping Oil Pressure Relief Valve


If new parts are being fitted to the oil pressure relief valve it will be necessary to lap the valve poppet
against the washer to ensure a good fit and seal. This is done by hand, using valve grinding paste to
bed the parts together.
After lapping ensure that all parts are thoroughly cleaned to remove all valve grinding paste.
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Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Fit the components of the valve as shown in Figure 198. Ensure the circlip is fitted with the flat face
outwards and the curved face inwards – and that it “snaps” into position clearly when fitting.
Press and release the poppet a few times to make sure everything is working as it should.
As a starting point it is recommended to not fit any washers underneath the spring. After the initial test
run washers can be added to fine-tune the engine’s oil pressure.
Figure 198 – Oil Pressure Relief Valve Assembly
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Jabiru 2200 & 3300 Aircraft Engines
8 Post-Assembly
8.1

Oils
During initial running a non-detergent oil must be used to encourage proper bedding-in of components.
Oils must meet the following standards:
- Aero Oil W Multigrade 15W-50, or equivalent Lubricant complying with MIL-L-22851C, or
- Lycoming Spec. 301F, or
- Teledyne–Continental Spec MHF-24B
Table 7 shows oil recommendations for initial running. We recommend Aero Shell 100, Exxon Aviation
Oil 100 or BP Aviation Oil 100.
This oil must be used for the first 25 hours of operation after a top end inspection or overhaul or
whenever new or honed cylinders are fitted.
For further information on oils to use refer to the Jabiru Instruction & Maintenance Manual appropriate
to the engine.



Table 7 – Oil Recommendations for Run-In.
Oil Weight:
80
100
120
Outside Air Temperature
-17°C to 25°C
(1° to 77°F)
15°C to 35°C
(59° to 95°F)
Above 35°C
(95°F)
WARNING
Automotive oils MUST NOT be used. Automotive oils are not designed for the unique environment
of an air-cooled aero engine and have proven to give disastrous wear rates.
8.2


Before First Start
Check oil pressure. The simplest way to do this test is to remove a spark plug from each cylinder,
then use the starter motor to spin the engine until the oil pressure reading comes up. Alternatively an
external oil pressure source can be plumbed into the engine. This test ensures that the oil circuit of the
engine is working properly before starting – if a fault in the oil circuit was found with the engine running
damage to the main bearings etc is very likely.
Install to a suitable running rig. Engines can be run-in on the ground on a test rig – however it is
essential that this rig have oversize cooling ducts for the cylinder heads and for the oil cooler. Normal
aircraft ducts are not enough – running an engine on the ground using aircraft cooling ducts can quickly
overheat and ruin an engine.
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Tacho
Oil Temp & Pressure
CHT Gauges X6
Thermocouple Monitor for
Carby Inlet Air Temp
Oil Cooler
Figure 199 – Engine Ground Running Rig

8.3
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Fit a suitable propeller. Carrying on from the last point, if the engine is being run on the ground then a
suitable “club” prop must be fitted. A club prop must allow the engine to reach a minimum of 3250 RPM
and a maximum of 3400 RPM. A prop which does not meet either of these limits will not load the
engine correctly and can initiate long-term operating issues.
Ground Run-In & Test Procedures
Test running is an essential part of the full overhaul or top end overhaul process. It is worth spending
extra effort during this testing to catch any small issues which may grow more serious in operation.
At the completion of assembly of the engine after overhaul, it is recommended that the engine be
mounted upon a suitable test stand for its initial or run-in operation.
Alternately the engine may be re-fitted to the aircraft and run. While the very first runs may take place
on the ground in an airframe, any further testing must be carried out in the air to ensure sufficient airflow
for engine cooling.
The run-in serves a two-fold purpose; first, to seat piston rings and burnish any new parts that have
been installed and second, to give the operator control over the first critical hours of operation, during
which time he can observe the functioning of the engine by means of the test cell instruments or, if the
engine is re-fitted to the aircraft, the aircraft instrumentation.
Also at this time any malfunctions can be corrected and oil leaks repaired.
The first few hours after an overhaul are critical for the rest of the life of the engine and no effort should
be spared to conduct engine running according to the following criteria. What follows is a very specific
set of power settings, typically periods of full power operation followed by reduced power periods to
ensure correct cooling. If these instructions are followed to the letter the rings will bed into the cylinders
correctly and this will result in a much more pleasant engine with a decent life expectancy provided that
our daily inspection and maintenance procedures are followed. A sample ground run-in procedure is
included in the engine overhaul booklets in Section 9 below.
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8.4
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Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
On completion of the run post-run-checks must be carried out – refer to Sections 9.9.10 and 0 for
details.
Final Tasks
Unless the engine is to be fitted to an aircraft and used immediately it must be inhibited to prevent
corrosion. Engines which have just been run-in are very susceptible to corrosion and so must be
inhibited immediately that post-run checks have been completed. Details are included in Section 0.
Thoroughly clean engine
Apply caps to all engine openings: carburettor air intake, fuel pump and carburettor fuel fittings, engine
crankcase breather, exhaust tubes, oil cooler adaptor fittings.
Apply a warning tag to the engine. The tag should state, at a minimum:
- ENGINE RUN-IN COMPLETED.
- ENGINE OIL DRAINED
- CORROSION INHIBITOR APPLIED
- DO NOT RUN ENGINE UNTIL ALL CAPS HAVE BEEN REMOVED AND OIL HAS BEEN ADDED
TO THE SUMP.
Finally, the documentation must be completed. Build sheets and test cards must be filled out. Normally
the statement or report given to the customer will include lists of the new parts fitted. The build sheets
used by Jabiru Aircraft are all included in Section 9 and it is strongly recommended that these are used.
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Engine Overhaul Manual
JEM0001-8
8.5
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Troubleshooting
Table 8 - Troubleshooting
Symptom
Suggestion
Poor cold starting
1.
2.
3.
4.
5.
6.
7.
8.
Check starter motor and overhaul if required
Check battery health
Old spark plugs or plug gap too large
Battery too far from starter motor, loss of power due to cable resistance.
Incorrect oil grade for the temperature. Multigrade preferred.
Confirm tuning correct
Do not use choke & throttle together during start attempts.
Check choke jet is drilled to approx 1.2mm
Low oil pressure
1.
2.
3.
4.
Oil pressure relief valve needs cleaning or re-seating
Gauge error
Cavitation on oil pump feed – oil pickup needs re-sealing
Excess internal clearances
High CHT
1.
2.
3.
4.
5.
CHT sender not perfectly centred over spark plug.
Poor installation of engine to aircraft. See Jabiru Engine Installation Manual
Valves not seating – adjust
Tuning incorrect
Propeller sizing wrong – engine overloaded
High oil usage
1.
2.
3.
4.
5.
Worn valve guides
Worn or stuck piston rings
Worn, glazed or out-of-round cylinder barrels
Poor engine installation – incorrect oil vent location
Use of oil additives
High oil temperature
1. See rocker chamber vent Service Bulletin (for certain 2200 engines)
2. Poor engine installation - See Jabiru Engine Installation Manual
3. Oil level too high
“Missing” in flight
1.
2.
3.
4.
5.
6.
Carburettor flooding
1. Electric fuel pump giving too much pressure (must be less than 4psi)
2. Carby float needle seat scratched or incorrect size
Broken through-bolts
1. Detonation, most likely due to incorrect tuning
2. Over-tensioning
3. Re-use of bolts / studs at overhaul.
Flywheel Attachment
Damage
1.
2.
3.
4.
5.
Valve Failure
1. Carburettor tuning – running too lean
2. Poor valve adjustment
3. Excess valve guide wear
Excess Metal in Oil Filter
1. Corrosion in cylinder barrels
2. Dirty oil
Carby ice
Ignition coil gap needs adjusting, defective coil
Replace spark plugs
Check ignition leads for fretting or shorts
Carburettor float level too low or too high.
Tuning incorrect
Incorrect propeller choice
Prop strike or other engine damage
Detonation
Loose or poorly maintained propeller
Incorrect Loctite / installation
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JEM0001-8
Symptom
Piston Pick Up
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Suggestion
3. Cam / lifter face wear. Pushrod wear
4. Note that a certain amount of metal in the filter is normal for a Jabiru engine
due to the piston ring / cylinder materials used.
1. Incorrect piston / cylinder sizing
2. Lack of oil
3. Overheating, especially during ground running
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Engine Overhaul Manual
JEM0001-8
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
9 Appendix A - Build Sheets & Test Cards – APPROVED SECTION
9.1
9.1.1
Torque Settings
Table of Torque Specifications
Table 9 – Torque Specifications
Part
Nom. Dia
Torque: nm
Torque ft.lbs
Alternator & coil mount bolts
1/4"
14
(10)
Camshaft gear bolts (lock wired)
1/4"
11
(8)
Carburettor flange cap screws
1/4"
11
(8)
Connecting rod cap screws
5/16”
24
(18)
Crankcase main studs / through bolts
3/8"
7/16”
47
58
(35)
(43)
Crankcase front studs
3/8"
7/16”
40
47
(30)
(35)
Propeller flange cap screws
3/8"
40
(30)
Cylinder head cap screws
5/16"
34
(24)
Engine mount plate bolts
1/4"
14
(10)
Engine mount plate bolts
5/16"
16
(12)
Flywheel-crank cap screws
5/16”
3/8”
34
40
(24)
(30)
Starfish – alloy flywheel cap screws
1/4”
11
(8)
Gearbox cover cap screws
1/4"
14
(10)
Oil Pump cap screws
5/16"
20
(15)
Jabiru Wooden Propeller bolts
1/4"
8
(6)
Starter motor cap screws
1/4"
14
(10)
12mm
16-19
(12-14)
Sump cap screws
1/4"
14
(10)
Tappet cover cap screws
1/4"
14
(10)
Mechanical fuel pump cap screws
5/16”
24
(18)
Cylinder Head Cap Screws
5/16”
34 Initial
27 after 25 hours
(24) Initial
(20) after 25 hours
Jabiru Propeller Bolts (using multiple
Belleville washers)
1/4"
8
(6)
Generic torque setting: ¼” UNC thread
1/4"
14
(10)
Generic torque setting: ¼” UNF thread
1/4"
14
(10)
Generic torque setting: 3/16” UNC thread
3/16”
8
(6)
Generic torque setting: 3/16” UNF thread
3/16”
8
(6)
Spark plugs: torque to value given OR
Tighten the plug until it contacts the head
then rotate it for another half turn (180°).
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Engine Overhaul Manual
Jabiru Aircraft Pty Ltd
JEM0001-8
9.2

Jabiru 2200 & 3300 Aircraft Engines
Build Tolerances
All dimensions are given in millimetres
Table 10 – Build Tolerances
Part
New Build
Top End
Overhaul
Prop flange run-out (Measured at outer diameter)
0.060 Max
Per New Build
Per New Build
Crankshaft run-out
0.050 Max
Per New Build
Per New Build
N/A
Per New Build
*See Note 1
Crankshaft Main journals
47.930 – 47.950
Full Overhaul
Crankshaft Big end journals
44.998 – 45.010
Per New Build
Per New Build
Crankshaft Thrust face
56.950 - 57.050
N/A
Per New Build
N/A
Per New Build
*See Note 1
N/A
Per New Build
*See Note 1
Crankcase Main bearing bores (no bearing)
Crankcase Main bearings (bearings fitted)
51.966 – 51.990
47.985 - 48.030
Crankcase Crank thrust (bearings fitted)
56.650 - 56.850
N/A
Per New Build
Crankcase Cam bearing bores
20.000 – 20.020
N/A
Per New Build
Crankcase Cam thrust face
14.95 – 15.10
N/A
Per New Build
Crankcase Lifter stems: solid lifter
8.965 - 8.990
N/A
Per New Build
Crankcase Lifter bores: solid lifter
9.000 - 9.050
N/A
Per New Build
Crankcase Lifter bores: hydraulic lifter
21.420 – 21.440
N/A
Per New Build
Connecting Rods Big Ends (no bearings)
48.015 – 48.030
Per New Build
Per New Build
45.040 - 45.070
Per New Build
*See Note 1
Per New Build
*See Note 1
23.02 – 23.03
Per New Build
Per New Build
109.95 – 110.05
Per New Build
Per New Build
N/A
Per New Build
*See Note 1
6.900 - 7.100
N/A
Per New Build
Camshaft Fuel pump lift
2.450 - 2.550 at pump
2.9 – 3.1 at cam
N/A
Per New Build
Camshaft Thrust faces
15.18 – 15.25
N/A
Per New Build
97.500 - 97.530
Per New Build
Per New Build
65.500
Per New Build
Per New Build
Pistons Pin diameter
22.990 - 23.000
Per New Build
Per New Build
Cylinder Bore diameter
97.610 – 97.630
97.610 –
97.700
Per New Build
Cylinder Length over flanges
106.95 – 107.00
N/A
Per New Build
Valves Stem diameter Inlet
6.970 - 6.990
Per New Build
Per New Build
Valves Guide ID Inlet
7.045 – 7.050
Per New Build
Per New Build
Connecting Rods Big ends (bearings fitted)
Connecting Rods Small ends
Connecting Rods Length between bore centres
Camshaft Journals
Camshaft Valve lift
Pistons Diameter
Pistons Height
19.94 – 19.95
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JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
Valves Stem diameter Exhaust
6.970 - 6.990
Per New Build
Per New Build
Valves Guide ID Exhaust
7.045 - 7.050
Per New Build
Per New Build
Valves Spring free length
38.000 - 40.000
Per New Build
Per New Build
Distributor Shaft diameter
14.94 – 14.97
N/A
Per New Build
15.000 - 15.030
N/A
Per New Build
Distributor Shaft end float
1.000 - 1.200
N/A
Per New Build
Fuel Pump Pushrod Type 1
72.75 – 72.85
N/A
Per New Build
Fuel Pump Pushrod Type 2
74.75 – 74.85
N/A
Per New Build
Pushrod length: solid valve lifters.
211.5 – 212.5
Per New Build
Per New Build
Pushrod length: hydraulic valve lifters, solid
pushrod.
215.2 – 215.3
Per New Build
Per New Build
Pushrod length: hydraulic valve lifters, hollow
pushrod.
214.7 – 215.3
Per New Build
Per New Build
Pushrod length: roller followers, hollow pushrod.
206.3 – 207.7
Per New Build
Per New Build
2200 Old Sump: Dipstick length from top of cap to
markings.
Full Mark: 279 – 281
Low Mark: 294 – 296
Per New Build
2200 New Sump: Dipstick length from top of cap
to markings.
Full Mark: 314 – 316
Low Mark: 329 – 331
Per New Build
3300 Sump: Dipstick length from top of cap to
markings.
Full Mark: 279 – 281
Low Mark: 294 – 296
Per New Build
Distributor Shaft post ID
Piston, gudgeon, circlip, connecting rod, big-end
bearing assembly weights – maximum difference
between lightest and heaviest assembly used in
engine
Per New Build
Per New Build
Per New Build
Per New Build
Up to 3g
Per New Build
*Note 1: Bearing journal sizes of early model engines differ slightly from those of later model engines. In
some cases journals outside the limits given may still provide bearing clearance within acceptable limits
when assembled with matching parts; i.e. an older crankshaft may measure slightly under the current lower
limit but provide acceptable clearance when used in a matching older crankcase. This is acceptable
practice and parts less than 0.05mm outside the size limits specified may be used, provided that the
requirements for bearing crush, bearing fit and bearing clearance are all met.
WARNING
This leeway applies only to those items specified in Table 10.
9.3
Multi-Cycle Items
Table 11 – Mandatory Replacement Items – Multi-Cycle Parts
Item
Reserved
9.4



Maximum Life
-
Compounds & Sealants
Specific compounds and sealants are specified in the assembly checklists given below.
Generic fastener retaining compound: Use Loctite 243 unless specified otherwise.
Retaining compound need not be used on fasteners with inbuilt locking (such as MS21042 type lock
nuts) unless specified otherwise.
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Engine Overhaul Manual
JEM0001-8
9.5


Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Maximum Allowable Clearances (Wear Limits)
All dimensions are given in millimetres
“New Build Clearances” assume use of all current-spec parts.
Table 12 – Clearance and Wear Limits
New Build
Clearances
Top End
Inspection
Full Overhaul
0.20 - 0.80
N/A
Per New Build
Main bearing Clearance
0.035 – 0.10
N/A
Per New Build
Big end bearing clearance
0.04 – 0.07
Per New Build
Per New Build
Big end bearing crush
0.05 – 0.20
Per New Build
Per New Build
Camshaft bearing clearance
0.05 – 0.08
N/A
Per New Build
Camshaft end float
0.05 - 0.50
N/A
Per New Build
Solid Lifter to crankcase
0.15
N/A
Per New Build
Hydraulic Lifter to Case
0.19
N/A
Per New Build
Piston to cylinder
0.08 – 0.13
0.08 – 0.15
Per New Build
Piston compression ring end gap
0.40 - 1.20
N/A
Per New Build
Piston compression ring side clearance
0.08 - 0.12
N/A
0.05 – Early model
0.08 - 0.12 – Late
model
0.04
Per New Build
Per New Build
Inlet valve stem to valve guide
0.055 – 0.08
0.10 Max
Per New Build
Exhaust valve stem to valve guide
0.055 – 0.08
0.10 Max
Per New Build
Distributor shaft/post
0.03 – 0.09
N/A
0.03 – 0.15
Distributor shaft end float
0.5 – 1.20
N/A
Per New Build
Rocker shaft to rocker arm
0.12 – 0.18
Per New Build
Per New Build
Oil pump housing to outer rotor clearance
0.05 – 0.15
Per New Build
Per New Build
Oil pump inner rotor to outer rotor clearance
0.03 – 0.08
Per New Build
Per New Build
0.030 – 0.006
Per New Build
Per New Build
Ignition coil gap
0.25 – 0.30
(0.010” – 0.012”)
Per New Build
Per New Build
Spark Plug Gap
0.53 - 0.58
(0.021” - 0.023”)
Per New Build
Per New Build
0.23 – 0.30
Per New Build
Per New Build
Part
Crankshaft end float
Gudgeon pin to piston
Oil pump rotor end clearance (use a
straightedge across the housing to measure
this clearance as shown in Figure 200.)
Valve clearance (solid lifter engines)
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Engine Overhaul Manual
JEM0001-8
9.5.1
Jabiru 2200 & 3300 Aircraft Engines
Oil Pump Clearance Measurement:
Figure 200 – Oil Pump Details
9.6
Electrical System Specifications
Table 13 – Electrical System Specifications
Ignition
All Coils
Strong & continuous spark required with 8mm
gap when tested using coil tester (Figure 27)
Coil to flywheel gap
0.27mm
Ignition harness resistance
6.7 KΩ per 300mm length
Ignition magnet Strength (see Figure 201)
1.5 – 2.5kg.
to
0.30mm
Alternator
Coil resistance: early 2200 (10 Pole)
0.5 Ω to
1.1 Ω
Coil resistance: Parallel Wound 12-Pole.
0.2 Ω to
0.5 Ω
Coil resistance –
Series Wound 12-Pole (per Document AVDALSR087)
1.4 Ω to
1.9 Ω
Coil earth resistance
Infinite
A.C. output: early 2200 (10 Pole)
30.0 VAC at 3000 RPM,
A.C. output: (2x6 parallel wound 12 pole)
30.0 VAC at 3000 RPM
A.C. output: (series wound 12 pole)
Up to 40.0 VAC at 3000 RPM
D.C. output
Up To 14.3 VDC at 3000 RPM
Maximum load: (10 pole)
10Amps continuous
Maximum load: (12 pole parallel and series)
17Amps continuous
Tachometer
Coil resistance
160 Ω to
170 Ω
Gap, flywheel tags to sender
0.40mm – 0.50mm
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Engine Overhaul Manual
JEM0001-8
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Figure 201 – Magnet Tests

Magneto and alternator magnets are tested using a prop bolt attached to a spring balance as shown
above: place the bolt on each magnet in turn and record the tension required to pull the bolt free from
the magnet. Tension requirement is detailed in Table 13.
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Engine Overhaul Manual
JEM0001-8
9.7
9.7.1
Jabiru 2200 & 3300 Aircraft Engines
Disassembly Record Sheet
Engine Details
Engine Serial #:
Date:
9.7.2 Engine Disassembly Record Sheet
 A disassembly control / record checklist is given below. This checklist describes disassembly as the
reverse of the assembly processes detailed in Sections 9.9.9 to 9.10.10. The assembly checklists
referenced need not be completed: completion of Table 14 is sufficient record of the disassembly.
 Where assembly checklists require measurements these steps may be skipped during disassembly.
 Where assembly checklists include the application of compounds these may be skipped during
disassembly.
 Where assembly checklists require stage inspections these may be skipped during disassembly.
 Disassembly for full overhaul as detailed. Disassembly for top-end overhaul may substitute Sections
9.10.2 to 9.10.7 in Table 14.
Table 14 – Engine Disassembly
No.
Details
Initials
Z1
Disassembly: Reverse process detailed in Build Sheet H
(Section 9.9.9, “Final Assembly”)
Z2
Disassembly: Reverse process detailed in Build Sheet G
(Section 9.9.8, “Fuel Pump & Carburettor”)
Z3
Disassembly: Reverse process detailed in Build Sheet F
(Section 9.9.7, “Gear Case”)
Z4
Disassembly: Reverse process detailed in Build Sheet E
(Section 9.9.6, “Flywheel, Ignition Coils, Starter Motor &
Alternator”)
Z5
Disassembly: Reverse process detailed in Build Sheet D
(Section 9.9.5, “Sump”)
Z6
Disassembly: Reverse process detailed in Build Sheet C
(Section 9.9.4, “Pistons, Cylinder & Cylinder Heads”)
Z7
Crankshaft Disassembly: Reverse process detailed in
Build Sheet B (Section 9.9.3, “Crankcase & Camshaft
Assembly”)
Z8
Crankshaft Disassembly: Reverse process detailed in
Build Sheet A (Section 9.9.2, “Crankshaft, Propeller Mount
Flange & Conrods”)
Z9
Clean parts to be re-used.
Z10
Corrosion protect & store components as required.
Z11
Stage Inspection of Engine
Checked By
Date
I hereby certify that the engine has been disassembled, cleaned, corrosion protected and stored in
accordance with the current revision of the engine overhaul manual (JEM0001).
Signed:
Date:
for Jabiru Aircraft Pty Ltd
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Engine Overhaul Manual
JEM0001-8
9.8
Jabiru 2200 & 3300 Aircraft Engines
Sample Completed Build Sheet
Filled out by
overhauler
Filled out by
supervisor
Table 15 – Build Sheet A (EXAMPLE)
No.
Details
Para
Initials
A1
Inspect for Burrs, Oil Holes, Chamfers; Clean
Crankshaft, Conrods and Propeller Mount Plate
0.0
XYZ
1-1-13
A2
Inspect Oil Holes and insert Welch Plugs
0.0
XYZ
1-1-13
A3
Measure Crankshaft dimensions. (Includes crank
run-out)
0.0
XYZ
1-1-13
A4
Inspect and measure Propeller Mount Flange
(includes flange run-out)
0.0
XYZ
1-1-13
A5
Inspect and measure Conrods (includes bearing
crush, bearing clearance)
0.0
XYZ
1-1-13
A6
Temporarily Mount Propeller Mount Flange to
Crankshaft and bolt to stand
0.0
XYZ
1-1-13
A7
Fit the Conrods to the Crankshaft; Use Loctite
620 on the bolts and torque per Table 9
0.0
XYZ
1-1-13
A8
Record measurements & clearances in build
record sheet - Table 26. Ensure all
measurements and clearances are within the
appropriate limits given in Table 10 and Table 12
-
XYZ
1-1-13
A9
Stage A - Stage Inspection of Assembly
XYZ
Checked By
DPS
Date
1-1-13
I hereby certify that the above subassembly has been assembled in accordance with the current revision of
the engine overhaul manual (JEM0001).
Signed: XYZ
Date: 1-1-13
for Jabiru Aircraft Pty Ltd
Filled out by overhauler
MPI Release Note No.
9.9
9.9.1
1234578910
Jabiru Engine Build Booklet
Engine Details
Engine Serial #:
Date:
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9.9.2
Jabiru 2200 & 3300 Aircraft Engines
Subassembly A Build Sheet – Crankshaft, Propeller Mount Flange and Conrods
Table 16 – Build Sheet A
No.
Details
Para
A1
Inspect for Burrs, Oil Holes, Chamfers; Clean
Crankshaft, Conrods and Propeller Mount Plate
5.9
A2
Inspect Oil Holes and insert Welch Plugs
Initials
Checked By
Date
5.9,
7.1
A3
Measure Crankshaft dimensions. (Includes crank
run-out)
5.9
A4
Inspect and measure Propeller Mount Flange
(includes flange run-out)
5.9
A5
Inspect and measure Conrods (includes bearing
crush, bearing clearance)
5.9,
7.1
A6
Temporarily Mount Propeller Mount Flange to
Crankshaft and bolt to stand
7.1
A7
Fit the Conrods to the Crankshaft; Use Loctite
620 on the bolts and torque per Table 9
7.1
A8
Record measurements & clearances in build
record sheet - Table 26. Ensure all
measurements and clearances are within the
appropriate limits given in Table 10 and Table 12
-
A9
Stage A - Stage Inspection of Assembly
I hereby certify that the above subassembly has been assembled in accordance with the current revision of
the engine overhaul manual (JEM0001).
Signed:
Date:
for Jabiru Aircraft Pty Ltd
MPI Release Note No.
(N/A for new engine builds)
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Engine Overhaul Manual
JEM0001-8
9.9.3
Jabiru 2200 & 3300 Aircraft Engines
Subassembly B Build Sheet – Crankcase and Camshaft Assembly
Table 17 – Build Sheet B
No.
Details
Para
B1
Inspect case, deburr, clean, check oil holes
5.10
B2
Fit inner crankcase “O” rings
7.2
B3
Fit all studs. Use Loctite 620 on threads.
7.2
B4
Fit crankcase dowls
7.2
B5
Blue and fit bearing shells
7.2
B6
Assemble and torque
7.2
B7
Measure main bearings
7.2
B8
Measure Cam Follower Bores
7.2
B9
Disassemble
7.2
B10
Fit oil relief valve, oil pressure sender and
pressure switch. Use Loctite 262 to seal pressure
sender & switch.
7.2
B11
Fit Solid Lifters
7.2
B12
Check Camshaft End Float
7.2
B13
Check Crankshaft End Float
7.2
B14
Record measurements & clearances in build
record sheet - Table 26. Ensure all measurements
and clearances are within the appropriate limits
given in Table 10 and Table 12
B15
Stage B - Stage Inspection of Assembly
Initials
Checked By
Date
-
I hereby certify that the above subassembly has been assembled in accordance with the current revision of
the engine overhaul manual (JEM0001).
Signed:
Date:
for Jabiru Aircraft Pty Ltd
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Engine Overhaul Manual
JEM0001-8
9.9.4
Jabiru 2200 & 3300 Aircraft Engines
Subassembly C Build Sheet – Pistons, Cylinders and Cylinder Heads
Table 18 – Build Sheet C
No.
Details
Para
C1
Clean and deburr all parts
5.11
C2
Install pushrod tube ‘O’ Rings, springs, washers
and circlips
7.3
C3
Check valve seats, fit spring retainers, install
valves
7.3
C4
Complete rocker shaft and rocker assemblies
7.3
C5
Fit cylinder base ‘O’ rings
7.3
C6
Measure and fit front piston circlip
7.3
C7
Check ring end gaps, fit rings to pistons
7.3
C8
Fit cylinders to heads. Torque per Table 9
7.3
C9
Install piston assembly to cylinder just clear of the
oil ring
7.3
-
C10
Record measurements & clearances in build
record sheet - Table 26. Ensure all
measurements and clearances are within the
appropriate limits given in Table 10 and Table 12
C11
Stage C - Stage Inspection of Assembly
Initials
Checked By
Date
I hereby certify that the above subassembly has been assembled in accordance with the current revision of
the engine overhaul manual (JEM0001).
Signed:
Date:
for Jabiru Aircraft Pty Ltd
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Engine Overhaul Manual
JEM0001-8
9.9.5
Jabiru 2200 & 3300 Aircraft Engines
Subassembly D Build Sheet – Sump
Table 19 – Build Sheet D
No.
Details
Para
D1
Clean and inspect the sump.
5.12
D2
Clean out blind threads using a suitable sized tap
5.12
D3
Ensure all seals and gaskets on plugs and
terminals are serviceable.
5.12,
7.4
D4
Stage D - Stage Inspection of Assembly
Initials
Checked By
Date
I hereby certify that the above subassembly has been assembled in accordance with the current revision of
the engine overhaul manual (JEM0001).
Signed:
9.9.6
Date:
for Jabiru Aircraft Pty Ltd
Subassembly E Build Sheet – Flywheel, Ignition Coils, Starter Motor And Alternator
Table 20 – Build Sheet E
No.
Details
Para
E1
Clean and de-burr starter ring gear & bendix
gears.
5.13
E2
Assemble magnets, pole plates, tacho tags and
alternator rotor to flywheel
5.13
E3
Verify magnet strength and polarity correct
5.13
E4
Check condition of starter motor and bendix
clutch, fit new bushes if required or replace
5.13
E5
E6
Assess fit of flywheel dowels
Initials
Checked By
Date
5.13,
7.5
Stage E - Stage Inspection of Assembly
I hereby certify that the above subassembly has been assembled in accordance with the current revision of
the engine overhaul manual (JEM0001).
Signed:
Date:
for Jabiru Aircraft Pty Ltd
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JEM0001-8
9.9.7
Jabiru 2200 & 3300 Aircraft Engines
Subassembly F Build Sheet – Gear Case
Table 21 – Build Sheet F
No.
Details
Para
F1
Deburr, clean and inspect all of the gears
5.14
F2
Measure the shaft post internal diameters and the
distributor shaft diameters
5.14
F3
Using loctite 515 fit the shaft posts to the gear
housing
5.14
F4
Fit the distributor shaft seals and rear crankshaft
seal
7.6
F5
Fit shafts to gears
5.14
F6
Fit the distributor shafts and gears to the gear
housing
5.14
F7
Check End Clearance of Distributor Shaft to Case
Flange
5.14
F8
Record measurements & clearances in build
record sheet - Table 26. Ensure all measurements
and clearances are within the appropriate limits
given in Table 10 and Table 12
-
F9
Stage F - Stage Inspection of Assembly
Initials
Checked By
Date
I hereby certify that the above subassembly has been assembled in accordance with the current revision of
the engine overhaul manual (JEM0001).
Signed:
Date:
for Jabiru Aircraft Pty Ltd
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Engine Overhaul Manual
JEM0001-8
9.9.8
Jabiru 2200 & 3300 Aircraft Engines
Subassembly G – Fuel Pump and Carburettor
Table 22 – Build Sheet G
No.
Check
Size
Para
G1
Main Jet
5.15
G2
Needle Jet
5.15
G3
Idle Jet
5.15
G4
Needle
5.15
G5
Float seat ___ mm dia
5.15
G6
Gravity Feed Valve 47-969
5.15
G7
Air Bleed 1.6mm
5.15
G8
Idle Mixture Screw Out 1 Turn
5.15
G9
Choke Jet 1.2mm
5.15
G10
Record measurements & clearances in
build record sheet - Table 26. Ensure
all measurements and clearances are
within the appropriate limits given in
Table 10 and Table 12
G11
Stage G Assembly
Stage
Inspection
Initials
Checked By
Date
-
of
I hereby certify that the above subassembly has been assembled in accordance with the current revision of
the engine overhaul manual (JEM0001).
Signed:
Date:
for Jabiru Aircraft Pty Ltd
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Engine Overhaul Manual
JEM0001-8
9.9.9
Jabiru 2200 & 3300 Aircraft Engines
Subassembly H – Final Assembly
Table 23 – Build Sheet H
No.
Details
Para
H1
Apply Loctite 515 to crankcase halves; lubricate where
necessary
7.8
H2
Locate camshaft in crankcase half
7.8
H3
Locate 2 crankcase halves over crankshaft
7.8
H4
Stage H1 - Stage Inspection of Assembly
-
H5
Apply Loctite 518 to cylinder base flanges
7.8
H6
Tension front (2) and rear (2) crankcase studs
7.8
H7
Place all through bolts in crankcase for cylinder bases
7.8
H8
Fit piston and cylinder Assemblies. Check circlips
7.8
H9
Stage H2 - Stage Inspection of Assembly
H10
Tension the cylinder base studs/bolts
7.8
H11
Fit pushrods and valve gear. Set gap per Table 12
(solid lifter engines)
7.8
H12
Apply Loctite 515 to sump sealing faces & fit to cases.
7.8
H13
Apply Loctite 515 to induction manifold sealing faces.
Assemble and fit to sump.
7.8
H14
Apply Loctite No. 2 to induction tubes & fit to induction
manifold.
7.8
H15
Check camshaft timing
7.8
H16
Apply Loctite 515 to sealing faces and fit engine mount
plate and gearbox housing
7.8
H17
Fit flywheel, alternator mount plate and ignition coils
7.8
H18
Fit Carburettor assembly
7.8
H19
Fit fuel pump. Apply Loctite 515 to sealing faces.
Apply Loctite 243 on fuel pump screws.
7.8
H20
Fit oil pump assembly. Apply Loctite 515 to sealing
faces.
7.8
Fit front seal and propeller flange. Torque per Table 9
Apply Loctite 515 to sealing faces.
7.8
Fit exhaust system
7.8
Initials
Checked By
Date
-
Stage H3 - Stage Inspection of Assembly
I hereby certify that the above subassembly has been assembled in accordance with the current revision of
the engine overhaul manual (JEM0001).
Signed:
Date:
for Jabiru Aircraft Pty Ltd
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Engine Overhaul Manual
JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
9.9.10 Ground Run-In Procedure
Table 24 – Ground Run-In Procedure
Pre Run-In Checks:
Correct Oil Type & Quantity
Idle Set
All connections secure
Propeller Secure
Oil Pressure
Time
Duration
Condition
(minutes)
RPM
RPM
CHT 4/6
Oil Temp
(220 – 525 kPa, solid lifter)
(100 – 180°C)
(50 – 118°C)
(220 – 350 kPa, hydraulic lifter)
Idle Min 80 kPa
2
Start and Idle
1000 - 1200
4
Hot Idle Check 1
1400
2
Very High Idle
1800
2
High Idle
1400
3
Mid Power
2000
2
High Idle
1600
2
60% Power
2400
2
High Idle
1800
2
70% Power
2600
2
Mid Power
2000
2
75% Power
2800
2
Mid Power
2200
2
85% Power
3000
2
Cooling Run
2000
4
75% Power
2800
2
Mid Power
2000
2
85% Power
3000
3
60% Power
2400
4
85% Power
3000
3
50% Power
2400
3
Takeoff Power
Full
2
60% Power
2600
2
Mid Power
2000
2
Cooling Run
1600
2
Hot Idle Check 2
Idle (800-1100)
O.A.T.
°C
Alternator:
V (AC), ___
V (DC) at 2800 RPM
Idle Comments:
Use:
Aero Shell 100/Exxon 100/BP Aviation Oil 100
2200
2.2 Litres or 2 Litres + Fill Oil Filter
3300 3.4 Litres or 3.2 Litres + Fill Oil Filter
Top End (RPM) Comments:
Overall Comments:
Any Changes / Adjustments Made During Run:
Magneto RPM Drop Left:
Magneto RPM Drop Right:
Post Run-In Checks:
Limits: 0 – 100 RPM
Test at 2000 RPM
Check for Oil Leaks
Adjust Valves (solid Lifter)
Re-Torque Cylinder Heads
Check Induction / Exhaust
Leak-down
#2
#3
#4
#5
#6
#1
80
80
80
80
80
80
test results
I hereby certify that this engine has been run in accordance with Jabiru requirements including the current
revision of Process Specification TR01 and is fit for use.
Signed:
Date:
for
Jabiru
Aircraft
Pty
Ltd
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Engine Overhaul Manual
JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
Engine Post Run Procedure – Stage J
Table 25 – Sheet J – Post Run Inspection
No.
Details
Para
J1
Heads re-torqued per Table 9. Valves adjusted (solid
lifter engines)
7.8
J2
Check induction/exhaust bolts
-
J3
Any changes to be made
-
J4
Rerun, check for oil leaks and/or any modifications
made (oil pressure/leaks etc)
-
J5
Check voltage output of alternator
Volts:
-
Leak Down Test Results:
-
J6
1
-
2
-
3
80
4
80
5
80
Initials
Checked By
Date
6
80
80
J7
Check all paper work
-
J8
Drain fuel/oil.
sealed
-
J9
Clean engine thoroughly.
-
J10
Remove spark plugs. Inhibit using a spray atomiser
with each piston in the down position. Rotate the
crankshaft 10 – 12 times. Use SHELL Aero fluid 2UN
(MIL-C-6529C Type 1) or similar engine corrosion
inhibitor. Install spark plugs and connect leads.
-
J11
Seal or cover all openings
-
J12
Attach a warning tag to the engine (oil drained
warning).
-
J13
Stage J - Post Engine Run Procedure Completed
Prepare for shipment, inhibited and
I hereby certify that the above Post Run Procedure has been carried out in accordance with the current
revision of the engine overhaul manual (JEM0001).
Signed:
Date:
for Jabiru Aircraft Pty Ltd
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Engine Overhaul Manual
JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
9.9.11 Jabiru Engine Build: Parts Measure and Clearance Record Sheet
Table 26 – Measure & Clearance Record Sheet
Engine No. (Include model)
P/No.
Crankshaft
1
Crank Mains:
Crank Run-Out:
Date:
2
Batch:
3
Item:
4
Comments
5
6
7
8
4
Item:
Item:
5
Comments
Comments
6
7
8
4
5
6
7
8
Prop Flange Run Out
Crankcase Left
Crankcase Right
Crankcase Assy
Main Tunnels
Clearances
P/No.
P/No.
1
2
Batch:
Batch:
3
1
2
3
Crankshaft
Crank Big Ends
Conrod Big Ends
Clearances
P/No.
1
1
Batch:
2
2
Item:
3
3
Comments
4
4
5
5
6
6
1
2
3
4
5
6
Camshaft
Camshaft Journals
Camshaft Tunnel
Clearances
P/No.
1
1
2
2
3
3
Item:
4
4
Comments
5
5
6
6
7
7
8
8
1
2
3
4
5
6
7
8
Head 1
Head 2
Head 3
Head 4
Head 5
Head 6
In. Valve Guides
Ex. Valve Guides
In. Valves
Ex. Valves
In. Clearances
Ex. Clearances
P/No.
P/No.
P/No.
P/No.
P/No.
P/No.
1
1
1
1
Batch:
Batch:
Batch:
Batch:
Batch:
Batch:
2
2
2
2
Item:
Item:
Item:
Item:
Item:
Item:
3
3
3
3
Comments
Comments
Comments
Comments
Comments
Comments
4
4
4
4
5
5
5
5
6
6
6
6
1
2
3
4
5
6
1
2
3
4
5
6
Cylinder Barrel 1
Cylinder Barrel 2
Cylinder Barrel 3
Cylinder Barrel 4
Cylinder Barrel 5
Cylinder Barrel 6
Barrel 1
Barrel 2
Barrel 3
Piston Diameters:
Clearance
P/No.
P/No.
P/No.
P/No.
P/No.
P/No.
Bore:
Bore:
Bore:
1
Batch:
Batch:
Batch:
Batch:
Batch:
Batch:
Length:
Length:
Length:
2
Item:
Item:
Item:
Item:
Item:
Item:
Comments
Comments
Comments
Comments
Comments
Comments
3
4
Bore:
Bore:
Bore:
5
Length:
Length:
Length:
6
1
2
3
4
5
6
Ring Gap Top
Ring Gap Bottom
1
2
3
4
5
6
1
2
3
4
Batch:
Barrel 4
Barrel 5
Barrel 6
Comments:____________________________________________________________________________
I hereby certify that the above parts have been measured, engraved & installed as recorded.
Signed:
Date:
for Jabiru Aircraft Pty Ltd
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Engine Overhaul Manual
JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
9.10 Top End Overhaul Booklet
9.10.1 Engine Details
Engine Serial #:
Date:
9.10.2 Top End Subassembly A Build Sheet – Conrods
Table 27 – Top End Build Sheet A
No.
Details
Para
A1
Clean Conrods
5.9
A2
Inspect and measure Conrods (includes bearing
crush, bearing clearance)
5.9,
7.1
A3
Fit the Conrods to the Crankshaft; Use Loctite
620 on the bolts and torque per Table 9
7.1
A4
Record measurements & clearances in build
record sheet - Table 26. Ensure all
measurements and clearances are within the
appropriate limits given in Table 10 and Table 12
-
A5
Stage A - Stage Inspection of Assembly
Initials
Checked By
Date
I hereby certify that the above subassembly has been assembled in accordance with the current revision of
the engine overhaul manual (JEM0001).
Signed:
Date:
for Jabiru Aircraft Pty Ltd
MPI Release Note No.
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Jabiru 2200 & 3300 Aircraft Engines
9.10.3 Top End Subassembly C Build Sheet – Pistons, Cylinders and Cylinder Heads
Table 28 – Top End Build Sheet C
No.
Details
Para
C1
Clean and deburr all parts
5.11
C2
Install pushrod tube ‘O’ Rings, springs, washers
and circlips
7.3
C3
Check valve seats, fit spring retainers, install
valves
7.3
C4
Complete rocker shaft and rocker assemblies
7.3
C5
Fit cylinder base ‘O’ rings
7.3
C6
Measure and fit front piston circlip
7.3
C7
Check ring end gaps, fit rings to pistons
7.3
C8
Fit cylinders to heads. Torque per Table 9
7.3
C9
Install piston assembly to cylinder just clear of the
oil ring
7.3
-
C10
Record measurements & clearances in build
record sheet - Table 26. Ensure all
measurements and clearances are within the
appropriate limits given in Table 10 and Table 12
C11
Stage C - Stage Inspection of Assembly
Initials
Checked By
Date
I hereby certify that the above subassembly has been assembled in accordance with the current revision of
the engine overhaul manual (JEM0001).
Signed:
Date:
for Jabiru Aircraft Pty Ltd
9.10.4 Top End Subassembly E Build Sheet – Starter Motor
Table 29 - Top End Build Sheet E
No.
Details
Para
E1
Fit new bushes and bearings to starter motor &
bendix gear assembly. Fit new brushes to motor
& re-assemble with Loctite 243
5.13
E6
Stage E - Stage Inspection of Assembly
Initials
Checked By
Date
I hereby certify that the above subassembly has been assembled in accordance with the current revision of
the engine overhaul manual (JEM0001).
Signed:
Date:
for Jabiru Aircraft Pty Ltd
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JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
9.10.5 Top End Subassembly F Build Sheet – Gear Case
Table 30 – Top End Build Sheet F
No.
Details
Para
F1
Deburr, clean and inspect all of the gears
5.14
F2
Measure the shaft post internal diameters and the
distributor shaft diameters
5.14
F3
Fit new crankshaft timing gear
7.6
F4
Using loctite 515 fit the shaft posts to the gear
housing
5.14
F5
Fit the distributor shaft seals and rear crankshaft
seal
7.6
F6
Fit shafts to gears
5.14
F7
Fit the distributor shafts and gears to the gear
housing
5.14
F8
Check End Clearance of Distributor Shaft to Case
Flange
5.14
F9
Record measurements & clearances in build
record sheet - Table 26. Ensure all measurements
and clearances are within the appropriate limits
given in Table 10 and Table 12
-
F10
Stage F - Stage Inspection of Assembly
Initials
Checked By
Date
I hereby certify that the above subassembly has been assembled in accordance with the current revision of
the engine overhaul manual (JEM0001).
Signed:
Date:
for Jabiru Aircraft Pty Ltd
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Jabiru 2200 & 3300 Aircraft Engines
9.10.6 Top End Subassembly G – Fuel Pump and Carburettor
Table 31 – Top End Build Sheet G
No.
Check
Size
Para
G1
Main Jet
5.15
G2
Needle Jet
5.15
G3
Idle Jet
5.15
G4
Needle
5.15
G5
Float seat ___ mm dia
5.15
G6
Gravity Feed Valve 47-969
5.15
G7
Air Bleed 1.6mm
5.15
G8
Idle Mixture Screw Out 1 Turn
5.15
G9
Choke Jet 1.2mm
5.15
G10
Record measurements & clearances in
build record sheet - Table 26. Ensure
all measurements and clearances are
within the appropriate limits given in
Table 10 and Table 12
G11
Stage G Assembly
Stage
Inspection
Initials
Checked By
Date
-
of
I hereby certify that the above subassembly has been assembled in accordance with the current revision of
the engine overhaul manual (JEM0001).
Signed:
Date:
for Jabiru Aircraft Pty Ltd
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Jabiru Aircraft Pty Ltd
Engine Overhaul Manual
JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
9.10.7 Top End Subassembly H – Final Assembly
Table 32 – Top End Build Sheet H
No.
Details
Para
H1
Place all through bolts in crankcase for cylinder bases
7.8
H2
Apply Loctite 518 to cylinder base flanges.
7.8
H3
Fit piston and cylinder Assemblies. Check circlips
7.8
H4
Stage H1 - Stage Inspection of Assembly
H5
Tension the cylinder base studs/bolts
7.8
H6
Fit pushrods and valve gear. Set gap per Table 12
(solid lifter engines)
7.8
H7
Apply Loctite 515 to sump sealing faces & fit to cases.
7.8
H8
Apply Loctite 515 to induction manifold sealing faces.
Assemble and fit to sump.
7.8
H9
Apply Loctite No. 2 to induction tubes & fit to induction
manifold.
7.8
H10
Apply Loctite 515 to sealing faces and fit engine mount
plate and gearbox housing
7.8
H11
Fit flywheel, alternator mount plate and ignition coils
7.8
H12
Fit Carburettor assembly
7.8
H13
Fit fuel pump. Apply Loctite 515 to sealing faces.
Apply Loctite 243 on fuel pump screws.
7.8
H14
Fit exhaust system
7.8
H15
Stage H3 - Stage Inspection of Assembly
Initials
Checked By
Date
-
I hereby certify that the above subassembly has been assembled in accordance with the current revision of
the engine overhaul manual (JEM0001).
Signed:
Date:
for Jabiru Aircraft Pty Ltd
9.10.8 Top End – Engine Ground Run-In Procedure
Use the procedure given in Table 24
9.10.9 Top End – Engine Post Run Procedure – Stage J
Use the procedure given in Table 25
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Engine Overhaul Manual
JEM0001-8
9.10.10
Jabiru 2200 & 3300 Aircraft Engines
Parts Measure and Clearance Record Sheet
Table 33 – Top End Measure & Clearance Record Sheet
Engine No.
Date:
Crankshaft
Crank Big Ends
Conrod Big Ends
Clearances
P/No.
1
1
Batch:
2
2
Item:
3
3
Comments
4
4
5
5
6
6
1
2
3
4
5
6
Head 1
Head 2
Head 3
Head 4
Head 5
Head 6
In. Valve Guides
Ex. Valve Guides
In. Valves
Ex. Valves
In. Clearances
Ex. Clearances
P/No.
P/No.
P/No.
P/No.
P/No.
P/No.
1
1
1
1
Batch:
Batch:
Batch:
Batch:
Batch:
Batch:
2
2
2
2
Item:
Item:
Item:
Item:
Item:
Item:
3
3
3
3
Comments
Comments
Comments
Comments
Comments
Comments
4
4
4
4
5
5
5
5
6
6
6
6
1
2
3
4
5
6
1
2
3
4
5
6
Cylinder Barrel 1
Cylinder Barrel 2
Cylinder Barrel 3
Cylinder Barrel 4
Cylinder Barrel 5
Cylinder Barrel 6
Barrel 1
Barrel 2
Barrel 3
Piston Diameters:
Clearance
P/No.
P/No.
P/No.
P/No.
P/No.
P/No.
Bore:
Bore:
Bore:
1
Batch:
Batch:
Batch:
Batch:
Batch:
Batch:
Length:
Length:
Length:
2
Item:
Item:
Item:
Item:
Item:
Item:
Comments
Comments
Comments
Comments
Comments
Comments
3
4
Bore:
Bore:
Bore:
5
Length:
Length:
Length:
6
1
2
3
4
5
6
Ring Gap Top
Ring Gap Bottom
1
2
3
4
5
6
1
2
3
4
Barrel 4
Barrel 5
Barrel 6
Comments:____________________________________________________________________________
I hereby certify that the above parts have been measured, engraved & installed as recorded.
Signed:
Date:
for Jabiru Aircraft Pty Ltd
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Engine Overhaul Manual
JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
10 Appendix B – Other Documentation
10.1 Job Traveller
Table 34 – Job Traveller
Jabiru Engine – Job Traveller
CASA VH Registration No. ……………………
Job Number:
Engine Model:
Form: JABENGJT-1
RA-Aus or Other Registration No. ……………….....
Order / Invoice No:
-2200
-3300
-5100
Engine Serial Number:
Date Received:
Owner:
TSO:
Work to be done (iaw Jabiru Approved Data & certified for in the applicable section of the engine overhaul booklet):
- Trade-In (Full Overhaul)
- Full overhaul & return to owner
- Top End Inspection
- Bulk Strip
- Maintenance (RA-Aus only)
- Other:
Records to be filed:
- Copy of ARC
- Copy of all job sheets
- Report to owner
- Job book, completed.
- Jabiru Engine Job Traveller
- Copy of specialist inspection reports - MPI etc.
- Copy of log book entry
Parts Shipped To Jabiru With Engine:
- Exhaust extractors
- Starter Motor
Use:
- School – mainly circuits
- School – even mix of circuits and cross-country
- Unknown
- Muffler
- Oil Cooler
- School – mainly cross-country
- Private
Reason for Overhaul:
-Time Expired
-Other:
-Update Spec
Since manufacture or its last overhaul has the engine had any of the following::
A prop strike or other accident?
-Yes
-No
Poor cylinder leak-downs?
-Yes
-No
High, low or fluctuating oil pressure?
-Yes
-No
Major work (i.e. top end overhaul)
-Yes
-No
High oil temperature?
-Yes
-No
Been hard to start when hot?
-Yes
-No
High cylinder head temperatures?
-Yes
-No
Been hard to start when cold?
-Yes
-No
Been using a Jabiru Prop?
-Yes
-No
If the engine has had major work, please give a quick
description of what was done and who carried it out:
Shipping Details:
Parts to be shipped to customer with engine:
Overhauled by:
-
- INHIBITED
-Exhaust extractors
-Starter Motor
-Jabiru;
Date:
-Muffler
-Oil Cooler
Signed by:
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JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
10.2 Summary of Parts Used

Note: Refer to lists in Sections 5.2 and 5.3 for parts which MUST be replaced at overhaul.
Table 35 – Summary of Parts Used
ENGINE NO:
Bulk Strip
Maintenance
Overhaul
Top End Overhaul
NEW
CRANKCASE
Main Bearings
Through Bolts
Engine Mount Plate
Pick Up Stainer
Oil Pressure Switch
Oil Pressure Sender
Oil Cooler Fitting
Valve Lifters
Tacho Pick-up
Oil Feed To Heads
Oil Pick-up
O Rings
CRANKSHAFT
Conrods
Conrod Bearings
Prop Drive
Front Seal
Crank Gear
CAM
CAM Gear Outer
CAM Gear Inner
FLYWHEEL
Magnets (ignition)
Vac Drive Plate
Ring Gear
ALTERNATOR
Magnet Ring
Stator
PISTONS
Rings
Gudgeons / Circlips
IGNITION HARNESS
Plugs
Rotors
Dizzy Caps
Dizzy Shafts
Dizzy Gears
Seals Dizzy
Rear Seals
Dizzy Case
Dizzy Posts
Coils
DATE:
Hydraulic
Solid Lifter
ORIGINAL
NEW
ORIGINAL
HEADS
Rockers
Shafts
O Rings
Collets
Valve
Springs
Adjustors
Solid Pushrods
Pushrod Tubes
Rocker Covers
Valve Guides
Rubber T’s
Lifter
CYLINDERS
O Rings
SUMP
Long Temp Sender
Swept Plenum Chamber
Induction Pipes
O Rings
Induction Gaskets
Heat Shield
Induction Hose Joiners
EXHAUST PIPES
Ex-Gaskets Type
Bevel Type
OIL COOLER
Oil Cooler Adaptor
Oil Hoses
FUEL PUMP
Push Rod
Gaskets / Spacer
STARTER MOTOR
Clutch Assy
OIL PUMP
Housing
Spacer Plate
Gears
CARBY
Fuel Line
Mount
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Engine Overhaul Manual
JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
10.2.1 Bulk Strip Checklist
Table 36 – Bulk Strip Checklist
Customer:
Engine Model:
2200A
2200J
2200C
3300A
3300L
Engine S/No.
Brief description of prop
strike:
No.
Details
Initials
1
Disassemble engine per Section 4
2
Original Prop Flange Engraving:
Measure Original Prop Flange Run Out:
mm
(Limits per Table 10)
Serviceable
Unserviceable
3
Where Used: New Prop Flange P/No:
New Prop Flange Engraving:
New Prop Flange Run Out:
4
5
Where Used: New Crankshaft P/No:
New Crankshaft Engraving:
New Crankshaft Run Out:
Assemble engine per Section 7.
7
Stage Inspection of Assembly
Date
mm
Original Crankshaft Engraving:
Measure Original Crankshaft Run Out:
mm
(Limits per Table 10)
Serviceable
Unserviceable
6
Checked By
mm
I hereby certify that the above subassembly has been assembled in accordance with the current revision of
the engine overhaul manual (JEM0001).
Signed:
Date:
for Jabiru Aircraft Pty Ltd
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JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
10.3 Job Summary Sheet
Table 37 – Job Summary Sheet
Customer:
Engine Model:
2200A
2200J
2200C
3300A
3300L
Engine S/No.
Work Performed:
Bulk Strip
Engine Run-In:
Table 24 (Ground Run Record) attached
Table 25 (Post ground run check sheet) attached.
Parts Used:
Table 35 (Summary of parts used) attached.
Bulk Strip Checklist:
Table 36 attached (where appropriate)
i.
ii.
iii.
iv.
v.
Top End Overhaul
Full Overhaul
Refer to engine maintenance manual (normally JEM0002) for initial running requirements for overhauled engines.
Engine shipped with NO OIL. Oil must be added to sump (2.2 L for 2200 engines, 3.3L for 3300) before starting.
Oil grade must comply with requirements of the engine maintenance manual (normally JEM0002).
All caps and covers must be removed from the engine before starting.
During shipping inhibitor may have collected in the carburettor. Inspect & clean carby if necessary before starting.
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JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
11 Appendix C - Wear Factors
11.1 Wear Factors



The following table shows typical wear amounts per 1,000 hours of operation, and is intended to all the
reader to assess the possibility of components achieving 1 or more cycles.
Note that these values are given as a guide only. Operation of engines with poor quality “dirty” oil/and
or corrosion mixed in with oil has elevated wear on contact surfaces. Many other environment-specific
factors will also vary the engine wear rates.
When carrying out a top end inspection, the overhauler must keep these factors in mind – for example a
cylinder measuring 97.65mm may be within the wear limits for the part but it will not survive another full
cycle. Parts which are unlikely to survive in service for another full cycle must be replaced.
Table 38 – Wear Factors
Part
Crankshaft end thrust
Crankshaft Main Bearings
Crankshaft Mains
Crankshaft Big Ends
Camshaft End Thrust
Camshaft Bearing Areas (5)
Camshaft Followers on Stem (Solid)
Camshaft Fuel Lobe
Connecting Rod Bearing
Crankcase Cam Tunnel
Crankcase Cam Follower Bores
Gudgeon Pin Diameter
Pump Push Rod Length
Distributor Posts
Distributor Shafts
Valve Rocker Shafts
Rocker Bushes (Hydraulic)
Rocker Bushes (Hydraulic – Pushrod Oil Feed)
Rocker Bushes (Solid)
Valve Stems Inlet
Typical Wear for 1 Cycle (1000 hours)
0.02
0.005 - 0.010
0 - 0.005
0.005 - 0.01
0.06
0.01
0.0 - 0.005
0.01
0.025 - 0.06
0.015
0.02 - 0.03 (Solid Lifter)
0.000 - 0.005
0.01 - 0.03
0.01 Typical
0.00 - 0.01
0.015
0.012 - 0.020
Approx ½ of above Hydraulic
0.06 - 0.10
0.00
Valve Stems Exhaust
0.00 - 0.01
Valve Spring Length
Shortened by 1.60 - 1.80
Cylinder Head Inlet Valve Seat
Visual
Cylinder Head Exhaust Valve Seats
Cylinder Head Inlet Valve Guides
Cylinder Head Exhaust Valve Guides
Oil Pump - Inner to Outer Gear
Cylinder Bore Wear
Piston Diameter
Piston Ring Sliding Clearances
Ring Gaps
Visual
0.01 - 0.02
0.01 - 0.02
0.025 - 0.08
0.01 - 0.03 (width and taper)
0.0 - 0.01
<0.01
1.50 Typical
Ring Gaps - On Oil Additive Engines
3.00 - 4.50
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Engine Overhaul Manual
JEM0001-8
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
12 Appendix D - Mandatory Replacement Parts
12.1 General

Note that while a reasonable stock of spare parts is kept, some older parts may no longer be produced.
Table 39 – Mandatory Updates
Item
Notes
-
Overall length of barrel and any shim used must be 107.0mm.
Spigot type must be used (no head gaskets)
-
Only steel “solid” cams must be used. Hollow cast items must be
replaced.
2200 Solid lifter engines must use cam P/No. 4738092
2200 Hydraulic lifter engines must use cam P/No. 4A432A0D
3300 Solid lifter engines must use cam P/No. 4625072
3300 Solid lifter engines must use cam P/No. 4A433A0D
-
2200 – P/No. 4A225A0D / 4A226A0N OR
2200 – P/No. 4A499A0D / 4A500A0N
3300 – P/No. 4A255A0D OR
3300 – P/No. 4A506A0D
Heads with “WELLTITE” valve seats only may be used.
-
2200: Cranks to be upgraded or replaced to use 5/16” (or 3/8”) flywheel
screws & 6mm dowels.
-
New port plate must be fitted or existing part modified to match current
porting specs. Details in body of this manual.
Oil Pressure Relief Valve
-
Brass poppets must be replaced with steel parts.
Flywheel
-
Mandatory upgrade to use 5/16” screws and 6mm dowels.
Recommended update to use “Starfish” steel attach adaptor system.
Pushrods
-
Solid lifter engines – P/No. 4642084
Hydraulic lifter engines, external oil pipe feed – P/No. 4A089B0D
Hydraulic lifter engines, hollow pushrod oil feed – P/No. 4A421D0D
Roller lifter engines – P/No. 4A536A0D
Rear Engine Mount Plate
-
Either type may be used (99 tooth or 101 tooth).
MUST match flywheel ring gear fitted to engine.
Rear Gear Box
-
Must have oil drain grooves in distributor bosses.
Valve Lifters
-
Solid lifter P/No. PG92324
Hydraulic P/No. PG4A019
Roller Follower: P/No. PE4A022A0D
Sump
-
2200 solid lifter may use 4A298A0D or 4823002
2200 Hydraulic lifter must use 4A298A0D.
3300 engine uses P/No. 960409X or 4A540A0D
All hydraulic lifters to be replaced at 1000 hours TIS.
-
2200: Bolt-on induction to be used (sumps with manifold cast in to be
replaced)
-
40mm type to be used, settings as detailed above.
-
Recommended upgrade to systems without gasket between head and
exhaust – both engines.
-
“Standard”, “2-inch” or “3-inch” extensions may be used.
Cylinders
Camshafts
Cylinder Heads
Crankshafts
Oil Pumps
Induction System
Carburettor
Exhaust System
Propeller Drive Flange
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Jabiru 2200 & 3300 Aircraft Engines
-
Solid lifter, coarse fin head – 4769094 / 477009N
Solid lifter, fine fin head – 4A268A0D / 4A268B0N
-
Hydraulic lifter, coarse fin head – 4A087A0D / 4A088A0N
Hydraulic lifter, fine fin head - 4A268A0D / 4A268B0N
Hydraulic lifter, fine fin head, pushrod oil feed - 4A520A0D / 4A520C0N
OR 4A422A0D / 4A423A0N
Valve Rocker Bushes
-
Hollow pushrod rocker bushes P/No. SAPG121415F
All other rockers – P/No. PG121414F
Valve Springs
-
“Hydraulic” type to be used for all engines.
Alternators
-
10 or 12 pole single phase – 3-phase alternators must be replaced.
Dipsticks
-
2200 engine, sump P/No. 4823002 requires P/No. 4533064
2200 engine, sump P/No. 4A298A0D requires P/No. 4A400A0D
3300 engine uses P/No. 4533064
Conrods
-
Alloy rods must be replaced with steel items.
Oil Feed To Rockers
-
Solid lifter engine must use external oil feed pipe.
Hydraulic lifter engines - external oil feed pipe may be retained.
Upgrading to hollow pushrod oil feed system is recommended.
-
Very early 2200 cases must be replaced.
All 3300 cases may be used if serviceable.
All cases must have oil drain holes under the mechanical fuel pump
All cases must have oil channels for the cam journals
Solid lifter parts are available.
-
Very early 2200 engines did not have a “Strainer” on the pickup pipe
intake. Upgrading to fitting a strainer is mandatory.
-
Confirm piston part number on order to ensure a proper match to the
rod/barrel/head combination used.
Ignition Coils
-
Shiny black coils marked “LEADING X” must be replaced.
Starter Motor
-
Bosch or Denso types may be used if serviceable.
Denso types have more power and give better starting.
Solid Lifter Valve Rockers
Valve Rockers
Crankcases
Oil Pick Up
Pistons
12.2 Camshaft


Solid lifter engines do not require camshaft mandatory updates beyond those listed in Table 39 below.
Hydraulic lifter engines require updating as detailed below and in Section 5.10.3
12.3 Crankcase
12.3.1 Maximum Surfacing / Decking Limit
 A maximum of 0.15mm may be taken from each case half over its life.
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JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
12.3.2 Fretting General Information
“Pulled up” metal
Raised ridge
Figure 202 – Crankcase Fretting




Cases which have suffered fretting can be identified as shown in Figure 202. There will be
characteristic markings on the crankcase joining face near the main bearing journals which can be felt
by scratching with a fingernail – the raised portions will be clearly evident.
Suspect cases can also be checked in the field by checking the torque of the bottom crankcase
through-bolts with the torque wrench set at 28lb.ft. These bolts are set at 30lb.ft during assembly so if
the nuts move at 28lb.ft it is a good indicator that the cases have fretted and are no longer seating
together securely.
An engine which operates for an extended period with fretting can lead to unrepairable crankcase
damage, through bolt failure and engine stoppage.
The main causes of crankcase fretting in the Jabiru Engines are:
a. Pre-ignition or detonation due to lean running, incorrect fuel, low octane fuel, contaminated fuels or
combinations.
b. Incorrect through-bolt torque or uneven bolt tensioning.
c. Reduced through-bolt tension due to cylinder base cracking
d. Cracked or broken through-bolts
e. Poorly matched case halves
f. An inadvertent lean run – for example due to a incorrectly set float level or partially blocked fuel
filter.
g. Running engines with high valve stem-to-guide clearances, promoting oil residue in the intake
system. This has the effect of reducing the octane number (or AKI) of the fuel and can lead to
detonation or pre-ignition.
12.3.3 Fretted Crankcase Repair
 Fretting can be repaired by surfacing (or “decking”) the crankcase, then line-boring the crankshaft and
camshaft tunnels. Surfacing should always take the bare minimum material to remain within the limits
set. Excess surfacing will lead to the sump and backing plate not fitting the cases, rendering them
unserviceable.
WARNING
This process requires specialist equipment, tools and training to be successful. Overhaulers must
not attempt this job without access to these items.
 First the crankcases need to be completely stripped. All bolts, studs, dowels, fittings and plugs must be
removed. Heat may be required to extract some items.
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Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Figure 203 – Stripping Crankcases






Cases must be surfaced using a special machine. Care must be taken to not exceed the maximum
allowable amount. Operators must take the minimum material required to remove the fretting damage –
usually removing less than 0.1mm of material is sufficient.
New crankcase through-bolts and studs must be fitted. The original parts must be discarded.
The original crankcase dowels can be re-used, however after the case has been surfaced they need to
be shortened slightly – 0.5mm – and radiused / de-burred on the modified end.
After surfacing the cases must be bolted together and line bored along the crankshaft and camshaft
tunnels.
After line boring the tunnels must be within the newly manufactured tolerance range – main bearing
tunnel is 51.976 to 52.000mm and 20.00 to 20.01mm for the cam tunnel.
During line boring all crankcase dowels, studs and through-bolts must be fitted and correctly tensioned.
WARNING
ALL through bolts and crankcase studs must be replaced in a fretted case.
The same process which damages the cases also damages the bolts and studs and bolt failures are
likely if they are re-used.
 After surfacing and line boring the case need to be thoroughly de-burred and cleaned. Remember to fit
the O-rings to the studs as required on permanent assembly. Refer to the main body of the manual
above for detailed instructions on how to carry out this work.
Figure 204 – De-Burring Crankcase After Surfacing & Line Boring
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Jabiru 2200 & 3300 Aircraft Engines
12.4 Crankshaft
12.4.1 Maximum Time In Service
 Jabiru Aircraft apply a maximum Time In Service of to a crankshaft as detailed in Section 9.3.
 Once a crankshaft reaches this Time In Service it must be discarded and replaced with a new item.
12.4.2 Dowel Pins
 Section 5.9.1.1 describes the difference between “old” and “new” crankshafts. “Old” type crankshafts
must be replaced with “new” type or re-worked to the “new” configuration.
 Most old crankshafts can be re-worked to new specifications. Any crank which has not exceeded its
maximum Time In Service and which uses 5/16” flywheel mounting cap screws may be re-worked as
detailed in Jabiru Procedure AVDALSR038.
 Details of this procedure are reproduced below for ease of reference.
12.4.2.1 General

This procedure is for the installation of crankshaft to flywheel dowels on the 2200 and 3300 Jabiru
engines.
12.4.2.2 Applicability


To be carried out at major overhaul (2000hs TSO) of Jabiru 2200 & 3300 engines.
2200A Engines
- up to S/No. 20571
3300A Engines
- up to S/No. 836.
See service bulletin JSB 012 for details.
12.4.2.3 Special Tools

The following special tools are required for this procedure.
a. Dowel Hole Drilling Fixture (P/No. 8A021B0D) - Figure 205.
b. 15/64” drill bit - Figure 206.
c. Spiral ream Diameter 6 Tolerance H7 - Figure 206
d. 4 x 1 1/2” x 5/16”UNF cap screws - Figure 206
e. 4 x 5/16” UNF nuts.
Figure 205 – Drilling Fixture – Crankshaft Side on Left, Flywheel Side On Right
1
Note that some early engines use ¼” bolts to attach the flywheel. These crankshafts cannot be drilled to accept
dowels. The crank must be replaced with a new part.
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Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Figure 206 – 15/64” Drill (Left), 6mm Ream (Centre), UNF Cap Screws (Right)
12.4.2.4 Procedure
12.4.2.4.1



Preparation
This procedure is normally scheduled to happen during the engine’s major overhaul – that is, when the
engine cases have been split and the crank removed.
If required, it is possible to drill the crank while it is still in the cases. To do this the timing gearbox must
be removed to allow removal of the cam gear and to expose the crank. Care must be taken to ensure
no swarf is allowed to enter the engine, and the engine must be restrained & supported as noted below.
The photographs used in this procedure were taken on a bench to give an idea of the procedure
involved. In practice, a good quality drill-press must be used. The engine/crankshaft or flywheel must
be carefully aligned with the drill axis and restrained to ensure it does not move.
12.4.2.5 Crankshaft.

The crankshaft should be drilled first. The drilling guide is a close fit on the end of the crankshaft and
should be placed gently by hand or pulled in squarely using the cap screws. Care must be taken, as
attempting to force the fixture onto the shaft may damage the crank. Line up the small hole in the
fixture with the corresponding hole on the crankshaft.
Dowel hole – there are 3 of these on the fixture.
Bolt hole – there are 6 of these on the fixture
Positioning hole in fixture – align with
timing hole in crankshaft.
Figure 207 – Guide positioned on crankshaft.

The 4 cap screws will need to be arranged as shown above so that they don’t foul the drill. As each
hole is drilled move two of the screws around so the next dowel hole can be accessed. Always keep
two of the bolts tight so the guide can’t move.
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Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Figure 208 – Drilling & Reaming Crankshaft – ILLUSTRATION ONLY.

Use of a suitable lubricant when drilling the crankshaft is recommended as it is a high grade steel. It
will also prolong the life of the drilling jig. Drill the crankshaft dowel holes 10 deep (i.e. 10mm of fulldiameter hole – the tip length of the drill is not counted in this length). When reaming, the guide is used
to ensure a straight entry for the ream. The first time the jig is used the ream will be quite tight in the
holes. Minimum ream depth into the crankshaft is 6.5mm – but due to the use of hand tools reaming to
7-8mm depth is recommended.
12.4.2.5.1


Flywheel.
Like the crankshaft, the flywheel needs matching dowel holes. When fitting the drilling guide to the
flywheel use the positioning hole to align it correctly. Use the 4 x 5/16” UNF screws used in the
crankshaft section above to hold the fixture to the flywheel – use nuts and washers on the rear side
(alternator side) of the flywheel. Move the bolts around so that there is a clear space around the hole
being drilled. Make sure two bolts always stay tight so that the guide can’t move.
Once the guide is in place, drill all the way through the flywheel for each of the dowel holes. Then ream
the holes using the guide to align the ream. Being aluminium it is very easy to ruin the fit of the hole if
the guide is not used.
Figure 209 – Aligning Guide & Fitting To Flywheel.
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Jabiru 2200 & 3300 Aircraft Engines
Figure 210 – Drilling & Reaming Flywheel – ILLUSTRATION ONLY.
12.4.2.6 Assembly.

Once the dowel holes have been drilled and before the engine is assembled, dowels and a new
vacuum pump drive (P/No. 4646084) and timing gear (P/No. 4643084) are required. The timing gear
cannot be drilled as it is hardened and Nitrided. Insert dowels once flywheel, vacuum pump drive and
timing gear are installed on crankshaft and loosely bolted up. Knock dowels through flywheel until their
tips are approximately 2mm recessed into the flywheel. Tighten flywheel bolts to specifications.
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JEM0001-8
Jabiru Aircraft Pty Ltd
Jabiru 2200 & 3300 Aircraft Engines
Figure 211 – Flywheel to crankshaft assembly drawing
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Engine Overhaul Manual
JEM0001-8
Jabiru 2200 & 3300 Aircraft Engines
13 Appendix E – History of Updates
13.1 Engine Serial Number Decode




All engines are allocated a master serial number at manufacture that is referred to as the “A number”:
2200 engines = 22A-XXXX, 3300 engines = 33A-XXXX, where “XXXX” is a sequential number.
Certified engines are then allocated an additional sequential number that is referred to as the “B
number”, “C number” (or in older engines the “J number”): 2200 engines = 22B-XXX, 3300 engines =
33L-XXX, where “XXX” is a sequential number.
All engine records require reference to the “A number”.
The master list of A numbers and the cross-reference to B (C or J) numbers is kept in the Jabiru
Engines department, and all enquiries should be directed there: [email protected]
Please note: Configuration detailed below is at time of new build and may have been changed with
service work. Also, Current means at time of issue of this Manual. Changes to this configuration
information may have occurred since. This information is a guide only and not a complete list of
configuration changes.
13.2 Update History Table
Table 40 – Update History
Component
Cylinders
Pistons
Cylinder Heads
Valve Rockers
Valve Adjusters
Valve Springs
Rocker Blocks
2200 S/No.
3300 S/No.
Details
01 – 106
Head gasket type.
107 – 127
Spigot type, 105.5mm long
128 – 831
832 – 3442
3443 - Current
3498 – Current
01 – 436
01 – 153
154 – 2289
2290 – Current
2391 - Current
437 – 1003
01 – 223
Suits steel rod. Crown height 64.0mm
1003 - Current
224 – Current
Suits steel rod. Crown height 65.5mm
01 – 106
107 – 224
225 – 644
645 – 657
01 – 47
48 – 52
659 – 709
53 – 118
710 – 1003
119 – 223
1004 - Current
224 – Current
2068 – 2439
-
2553 - Current
961 - Current
3358 – Current
01 – 188
189 – 307
308 – 658
2210 – Current
659 – 2552
53 – 960
2553 - Current
961 - Current
01 – 188
189 – 502
503 - Current
01 – 153
154 - Current
01 – 188
189 – 224
01 – 52
01 – 33
34 – Current
01 – Current
Spigot type, 106.5mm long
Spigot type, 107mm long
Spigot type, 107.5mm long
Base holes sized to suit 7/16” bolts
Suits alloy rods.
Head gasket type
Spigot type
Symmetric spigot type
Fin area enlarged
Fin area enlarged more, valve seats
widened
Fin area enlarged more
Combustion chamber geometry changed,
more fins added beside exhaust port.
Rocker cavity venting required
Fine finned heads. Altered oil feed tube
shape to heads.
Oil feed moved to hollow pushrods
10/12mm wide, 7mm lift, 5/16” adjusters
12mm wide, 3/8” adjusters, 9mm lift
15mm wide, 3/8” adjusters 9mm lift
15mm wide, 3/8 adjusters, 9mm lift offset
tips.
Increased offset to suit narrow finned
heads, Hollow.
5/16” allen key adjuster
3/8” allen key
3/8 slotted
Small type
Heavier type
Std block, small valves, 1:1 ratio
Std block, large valves
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Engine Overhaul Manual
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JEM0001-8
Component
Oil Pick Ups
Jabiru 2200 & 3300 Aircraft Engines
2200 S/No.
3300 S/No.
Details
225 - Current
01 – 042
43 – 307
01 – Current
Block machined as part of head
Part of crank case
Pick up from oil pump face
Same geometry but fitted to sump with a
pin
Pick up part of oil pump face
308 – 325
326 – 793
01 - 150
794 - Current
151 – Current
01 – 053
053 – 069
Oil Feed to Cylinder Heads
Connecting Rod
Crankshaft
Camshaft
Through-Bolts & Studs
Tacho Pick Up
070 – 261
262 – 473
01 – 38
541 – 3357
3358 – Current
01 – 436
437 - Current
01 – 042
043 – 436
437 – 2057
2058 – 2731
2732 – 3533
3534 – Current
3499 – Current
01 – 377
378 – 603
604 – 2849
2850 – 3049
3050 – 3595
3596 – Current
0 – 3467
3468 – 3498
3498 – Current
01 – 1003
38 – 2209
2210 – Current
1003 - Current
220 – Current
01 – Current
01 – 836
837 – 1521
1522 – 2465
2466 – Current
2446 – Current
01 – 1683
1684 – 1900
1901 –2538
2539 - Current
0 – 2370
2371 – 2390
2391 - Current
01 – 219
01 – 340
341 – 436
Flywheel
Oil Pump
Push Rods
Starter Motors
Induction Passage
437 - 2102
01 – 856
2103 - Current
857 -
0 – 2731
2732 – 3498
3499 - Current
0 – 1521
1522 – 2445
2446 – Current
2436 – 2573
2574 – Current
01 – 238
239 – 1957
01 – 794 – All
20mm wide
1958 - Current
795 - Current
01 – 352
353 – 3357
3358 – 3595
3596 – Current
01 – 728
729 – 1467
1468 - Current
01 – 728
01 – 960
2210 – 2539
2539 – Current
01 – 58
59 – 509
510 - Current
01 – 67
Same as above but with strainer added
Feed rockers from the top of the case at
each side
1 line from oil gallery with above
Oil feed from oil gallery both sides with
restrictor fitting
Oil feed by machined restrictor (requires
oil feeds connected to the heads)
Rubber “T” piece used in feed line.
Pushrod oil feed used.
Alloy rods
Steel rods
Short crank, ¼” flywheel screws
Long crank, ¼” flywheel screws
Long crank, 5/16” flywheel screws
Dowels added between flywheel & crank
“Starfish” attachment
3/8” flywheel screws
Dowels added ‘tween prop flange & crank
Cast cam, 21mm between profiles
Cast cam, 23mm between profiles
Machined billet steel cam, hardened
285 Single Ring Cam
260 Two-Ring Cam
Roller lifter & Cam.
3/8” MS21042-type nuts
3/8” 12-Point nuts, extended studs
7/16” nuts
Long post, senses starter ring gear teeth
Short post, senses 2 tags on rear of
flywheel
Resin keyed magnets, ¼ screws to crank
Steel keyed magnets, ¼ screws to crank
Steel keyed magnets, 5/16 screws to
crank
Flywheel screws torque to 24 instead of
18 lb.ft
Aluminium flywheel centre
“Starfish” flywheel centre, 20mm dowels.
“Starfish” flywheel centre, 24mm dowels.
20° BTDC Ignition timing
23° BTDC Ignition timing
See Crankshaft for intro of 3/8 screws
12mm wide rotors
14mm wide rotors
Oil port plate adjusted to reduce pressure
spikes
198 / 200mm hollow type
Machined from solid.
Hollow type
Hollow, shorter to suit Roller lifter & Cam.
Reworked gold end type
Bosch type
Nippon Denso type
Plenum chamber integral with sump
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JEM0001-8
Component
Carburettors
Alternators
Jabiru 2200 & 3300 Aircraft Engines
2200 S/No.
3300 S/No.
Details
729 - Current
68 – 2330
2331 - Current
Separate “Swept” plenum
Series III Induction Body
Bin 32mm
Bing 40mm
Bing 40mm with economy tuning
Tuning per JSB018 (richer economy kit)
Modified carby needle fitted, tuning
unchanged
Fuel float needle seat port increased to
2.4mm
01 – 698
699 – 1883
1884 – 2849
2850 – 2919
01 – 722
723 – 913
914 – Current
2920 - Current
914 – 1419
-
1420 - Current
01 – 2661
10-pole alternator
Low output
2662 - Current
01 – 2086
2087 - Current
Distributor Rotors
Distributor Plates
Valve Lifters
164 - Current
01 – 47
48 – 856
Engine Mount Plate
Exhaust Manifold
01 – 163
1597 – Current
0 – 2067
2068 – 2849
2850 – 3094
3-phase type
12 pole Single phase high output
Std mount plate (common with 2200)
Top mount holes raised 15mm
48 - 856
857 - Current
01 – 139
140 - Current
01 – 208
209 - Current
01 – 117
118 – 561
562 – 756
757 – Current
0 – 960
961 – 1683
1684 – 1900
Plates suit 99 tooth ring gear
Plates suit 101 tooth ring gear
Red rotors
Black rotors (GB73)
Std type posts
Shortened posts
Std exhaust system
Manifolds lengthened by 15mm
Gasket-less exhaust introduced
Extractor type exhaust introduced
Solid lifters
Hydraulic high-leak lifters, 0-ring cam
Hydraulic slow-leak lifters, 1-ring cam
Hydraulic slow-leak lifters, 2-ring cam
3095 - 3595
1901 – 2538
3596 – Current
01 – 1399
2539 - Current
1400 –
792 -
2553 - Current
-
Starter Ring Gear
01 – 2086
2087 - Current
01 – 856
857 - Current
Roller lifter & Cam.
Original finned sump
Extra cap screws under gearbox cover
holding sump to engine mount plate
Deep sump fitted. Rocker chamber
venting not needed with this sump
99 Tooth
101 Tooth
Ignition Leads
2552 - Current
1206 - Current
Black, spiral wound type
Slimline Bridging Washer
1669 - Current
572 - Current
New washer for cylinder head screws
01 – 2146
2147 - Current
01 – 2731
2732 - Current
01 – 876
877 - Current
01 – 1521
1522 - Current
3 hole type
2 hole type
Inbuilt
Push-in type
Sump
Intake Gaskets
Vacuum Pump Drive
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