(L)IO-360-M1A Operation and Installation Manual
Contents
1. 3MOd 1 A3IQOM a LV 33MOd3SHOH LHOIVYLS A8 8 V 1O3NNO2 0 OL N33SNV31 34055344 FF 8 303 SAND 13A31 V3S NO 31V20O1 553 3qQ 1l11V 3111O23H1 TINA NO V 314201 E dUunivis3dWal 5 Wd TWNLOV ONIA OL AGNLILIV T3A31V3S Figure 3 2 Sea Level and Altitude Performance Curve 21 SECTION I LYCOMING OPERATION AND INSTALLATION MANUAL OPERATING INSTRUCTIONS L IO 360 M1A This Page Intentionally Left Blank 22 LYCOMING OPERATION AND INSTALLATION MANUAL SECTION II L IO 360 M1A PREPARATION SECTION II PART 1 PREPARATION Page Preparation of Engine for Installation 25 25 Uninhibiting 25 Preparation of esssS soosoo ons sroto biaso tesies ootas 26 23 SECTION II LYCOMING OPERATION AND INSTALLATION MANUAL PREPARATION L IO 360 M1A This Page Intentionally Left Blank 24 LYCOMING OPERATION AND INSTALLATION MANUAL SECTION II L IO 360 M1A PREPARATION SECTION II2. 3 CVlimders uio t Rd 3 Valve Operating Mechanism 3 ss a w Saha ha iqi Sunius 3 Ee 3 Accessory 5 3 Connecting 4 CRURA 4 ascia 4 Cooline 4 Ind ction 4 Lubrication lu 5 SECTION I LYCOMING OPERATION AND INSTALLATION MANUAL DESCRIPTION L IO 360 M1A This Page Intentionally Left Blank LYCOMING OPERATION AND INSTALLATION MANUAL SECTION I L IO 360 M1A DESCRIPTION SECTIONI PART 1 DESCRIPTION The Lycoming L IO 360 M1A is a fuel injected direct drive four cylinder horizontally opposed and air cooled with a down exhaust This engine is supplied with a starter Mounting pad drives for two AN type accessories and a propeller governor are included FAA Type Certificate Num
3. 7 i 9 N ld H p 20 596 Vaiss TSI 7 a gt q E TER zu d EE PAYA eeu PH 82 1 eet Nt m u a ef TIER EC P NSS UL 3 m E im d 2 Figure 2 1 Dimensions 30 LYCOMING OPERATION AND INSTALLATION MANUAL SECTION II L IO 360 M1A PROCEDURES NOZZLE PRESSURE CONNECTION LIFTING STRAP PROPELLER GOVERNOR PAD LIFTING STRAP ENGINE MOUNTING BRACKETS 5 16 in OIL LEVEL GAGE AND OIL FILL TUBE OIL TEMPERATURE 22 i 21 Ad HZ IU 2 2 INS A 2 Jm Oe 3 oT I DM SI vi Nm SM Y I ENGINE MOUNTING BRACKETS Figure 2 2 Installation Left Side View 3l SECTION II LYCOMING OPERATION AND INSTALLATION MANUAL PROCEDURES L IO 360 M1A TACHOMETER CONNECTION OIL TEMPERATURE CLOCKWISE ROTATION 625 18N UNF 3B 1 ACCESSORY MOUNTING PAD BREATHER CONNECTION OIL COOLER RETURN 375 18 NPT OIL PRESSURE GROUND TERMINAL GAGE CONNECTION 125 24 CENTER OF MOUNTING BRACKET MAGNETO GROUND TERMINAL
4. 16 Fuel Mixture Leaning Procedure 16 Engine Flight Chart TTL T 17 Engine Shut DOWN 19 Performance HEVES 20 11 SECTION I LYCOMING OPERATION AND INSTALLATION MANUAL OPERATING INSTRUCTIONS L IO 360 M1A This Page Intentionally Left Blank 12 LYCOMING OPERATION AND INSTALLATION MANUAL SECTION I L IO 360 M1A OPERATING INSTRUCTIONS SECTIONI PART 3 OPERATING INSTRUCTIONS 1 GENERAL Close adherence to these instructions will greatly contribute to the long life economy and satisfactory operation of the engine NOTE YOUR ATTENTION IS DIRECTED TO THE WARRANTIES THAT APPEAR IN THE FRONT OF THIS MANUAL REGARDING ENGINE SPEED THE USE OF SPECIFIED FUELS AND LUBRICANTS REPAIRS AND ALTERATIONS PERHAPS NO OTHER ITEM OF ENGINE OPERATION AND MAINTENANCE CONTRIBUTES QUITE SO MUCH TO SATISFACTORY PERFORMANCE AND LONG LIFE AS THE CONSTANT USE OF CORRECT GRADES OF FUEL AND OIL CORRECT ENGINE TIMING AND FLYING THE AIRCRAFT AT ALL TIMES WITHIN THE SPEED AND POWER RANGE SPECIFIED FOR THE ENGINE DO NOT FORGET THAT VIOLATION OF THE OPERATION AND MAINTENANCE SPECIFICATIONS FOR YOUR ENGINE WILL NOT ONLY VOID YOUR WARRANTY BUT WILL SHORTEN THE LIFE OF YOUR ENGINE AFTER ITS WARRANTY PERIOD HAS PASSE
5. N Tc cuin um MAGNETO INTAKE PIPES ACCESSORY OIL SUMP MOUNTING PAD 2 FUEL INJECTOR Figure 2 3 Installation Rear View 32 LYCOMING OPERATION AND INSTALLATION MANUAL SECTION II L IO 360 M1A PROCEDURES 3 PRE OILING ENGINE PRIOR TO START A CAUTION To eliminate the possibility of high speed bearing failure resulting from insufficient lubrication during initial starts all aircraft engines must be pre oiled after an overhaul following oil cooler draining or replacement or whenever the oil lines have been disconnected WARNING If a propeller is installed remain clear of the propeller turning arc The propeller will turn during this procedure and could cause injury a Fill the oil cooler with oil b Remove one spark plug from each cylinder of the engine c If the aircraft is not equipped with an oil pressure gage remove the STD 1102 allen plug from the upper left front of the main galley aft of the propeller governor pad d Place the mixture control lever in the IDLE CUT OFF position and the fuel selector switch in the OFF position e Turn the engine with the starter or with an external power source if available until a minimum oil pressure of 20 Ib is indicated on the oil pressure gage or until there is a steady flow of oil from the opening on the engine Do not energize the starter for periods longer than 15 seconds Allow the
6. PART 1 PREPARATION OF ENGINE FOR INSTALLATION Each Lycoming engine undergoes a thorough preservative treatment before leaving the factory To protect the cylinders and related parts preservative oil is sprayed into each cylinder Careful uncrating and uninhibiting of the engine is very important to prevent any of the preservative oil from entering the induction system 1 UNCRATING The Lycoming L IO 360 M1A engine has been carefully packed for shipment to prevent damage in transit and to ensure that the engine reaches its destination in perfect condition NOTE Any engine that has been stored in a cold area must be brought into an area with a temperature of at least 70 F 21 C for 24 hours before uncrating If this is not possible the preservative oil in the engine must be warmed to facilitate draining by heating the cylinders with heat lamps a Remove the top of the crate and set it aside b Lift and set aside any packing materials from on top of the engine c Connect an engine lifting cable to a winch hoist or crane able to support a minimum load of 750 Ibs d Connect the engine lifting cable to the lifting lugs on the top of the engine e Lift the engine from the crate 2 UNIHIBITING ENGINE A CAUTION Do not rotate the crankshaft of an engine containing preservative oil before removing the bottom spark plugs Engine damage will result cavri N Avoid contact of preservation oil with painted surfaces
7. oil is noted clean reinspect and reinstall the intake pipes 3 PREPARATION OF FUEL INJECTOR a Remove the fuel inlet strainer and clean it with a hydrocarbon based solvent such as Varsol or equivalent Inspect the fuel supply lines fuel manifold throttle body and bullet nose venturi to ensure they are clean and dry Reassemble the injector Inject clean fuel into the fuel inlet connection with the fuel outlets uncapped until clean fuel flows from the outlets Do not exceed 15 psi inlet pressure Dispose of used engine preservative and solvents in accordance with all applicable federal state and local environmental regulations NOTE If a small amount of preservative oil remains in the engine it will not be harmful however during the first oil change the oil should be drained while the engine is hot This will remove any residual preservative oil 26 LYCOMING OPERATION AND INSTALLATION MANUAL SECTION II L IO 360 M1A PROCEDURES SECTION II PART 2 PROCEDURES Page Installing HIR 29 Connecting External ACCeSSOrieSsiiscsssecssssecssdssccccscasesscccaccsaissedeccscessascscesacecdsecsdesdecssaceuessddeccesecedsccscesesassescasa 29 Pre Oiling Engine Prior to Start 33 27 SECTION II LYCOMING OPERATION AND INSTALLATION MANUAL PROCEDUR
8. L IO 360 M1A Operation and Installation Manual July 2008 FAA Approved LWCONVIING 2008 652 Oliver Street on Sem Williamsport PA 17701 Part No 60297 36 L IO 360 M1A Operation and Installation Manual Lycoming Part Number 60297 36 2008 by Lycoming All rights reserved Lycoming and Powered by Lycoming are trademarks or registered trademarks of Lycoming Lycoming Engines a division of AVCO Corporation a wholly owned subsidiary of Textron Inc All brand and product names referenced in this publication are trademarks or registered trademarks of their respective companies For additional information Mailing address Lycoming Engines 652 Oliver Street Williamsport PA 17701 U S A Phone Factory 570 323 6181 Sales Department 570 327 7278 Fax 570 327 7101 Lycoming s regular business hours are Monday through Friday from 8 00 A M through 5 00 P M Eastern Time 5 GMT Visit us on the World Wide Web at http www lycoming com Lycoming is a Textron Company LYCOMING OPERATION AND INSTALLATION MANUAL L IO 360 M1A ATTENTION OWNERS OPERATORS AND MAINTENANCE PERSONNEL This manual contains a description of the engine its specifications and detailed information on how to operate and install it This manual is FAA Approved and complies with FAR 33 5 and is intended for use by owners pilots and maintenance personnel responsible for care of Lycoming powered aircraft Modifications and repair p
9. by blue paint between the shroud tubes and requires long reach spark plugs indicated by yellow paint between the spark plug and the rocker box cover Cylinder barrels are machined from a chrome nickel molybdenum steel forging with deep integral cooling fins The interiors of the barrels are ground and honed to a specified finish Valve Operating Mechanism The valve operating mechanism employs a conventional camshaft located above and parallel to the crankshaft The camshaft actuates tappets which operate the valves through push rods and valve rockers Roller tappets are used to compensate for any expansion or contraction occurring in the valve train SECTION I LYCOMING OPERATION AND INSTALLATION MANUAL DESCRIPTION L IO 360 M1A Crankcase The crankcase assembly consists of two reinforced aluminum alloy castings divided at the centerline of the engine and fastened together by a series of body fit through studs and bolts and nuts The mating surfaces of the two castings are joined without use of a gasket and the main bearing bores are machined for the use of precision type main bearing inserts The crankcase forms the bearings for the camshaft Crankshaft The crankshaft is made from a chrome nickel molybdenum steel forging and all journal surfaces are nitrided A system of dynamic counterweights eliminates torsional vibration Accessory Housing An accessory housing is machined from an aluminum alloy casting and is fastened to the
10. mixture in Full Rich d Where applicable Move the propeller control through its complete range to check operation and return to full low pitch position Full feathering check twin engine on the ground is not recommended but the feathering action can be checked by running the engine between 1000 1500 RPM then momentarily pulling the propeller control into the feathering position Do not allow the RPM to drop more than 500 RPM 15 SECTION I LYCOMING OPERATION AND INSTALLATION MANUAL OPERATING INSTRUCTIONS L IO 360 M1A e A proper magneto check is important Additional factors other than the ignition system affect magneto drop off They are load power output propeller pitch and mixture strength The important thing is that the engine runs smoothly because magneto drop off is affected by the variables listed above Make the magneto check in accordance with the following procedures 1 Controllable Pitch Propeller With propeller in minimum pitch angle set the engine to produce 50 6596 power as indicated by the manifold pressure gage Mixture control should be in the full rich position At these settings the ignition system and spark plugs must work harder because of the greater pressure within the cylinders Under these conditions ignition problems can occur Mag checks at low power settings will only indicate fuel air distribution quality NOTE Aircraft that are equipped with fixed pitch propellers or not equipped wit
11. rear of the crankcase and to the top of the oil sump The two magnetos and the fuel pump are mounted on machined pads on the accessory housing and provisions for two additional accessories are provided Connecting Rods Connecting rods are made in the form of H sections from alloy steel forgings They have replaceable bearing inserts in the crankshaft ends and split type bronze bushings in the piston ends The bearing caps on the crankshaft ends of the rods are retained by two bolts through each cap secured by nuts Pistons The pistons are machined from an aluminum alloy forging The piston pin is of the full floating type with a plug at each end of the pin The lubrication system in the L IO 360 M14A engine uses a wet sump Figure 1 1 shows a schematic diagram of the oil system Oil Sump The sump incorporates the usual oil drain plug oil suction screen fuel injector mounting pad and the conventional intake riser and intake pipe connectors Cooling System This engine is designed to be cooled by air pressure Baffles are provided to build up a pressure and force the air through the cylinder fins The air is then exhausted to the atmosphere through gills or augmenter tubes usually located at the rear of the cowling Induction System Lycoming L IO 360 M1A engines are equipped with a Precision Airmotive RSA type fuel injection system The system is based on the principle of measuring air flow and using the air flow signal in a st
12. D New engines have been carefully run in by Lycoming and therefore no further break in is necessary insofar as operation is concerned however operate new or newly overhauled engines using only the recommended lubricating oils Refer to Oil Requirements Section 8 d NOTE Cruise at 6596 to 7596 power until a total of 50 hours has been accumulated or the oil consumption has stabilized This is to insure the proper seating of the rings as is applicable to new engines and engines in service following cylinder replacement or top overhaul of one or more cylinders The minimum fuel octane rating is listed in the flight chart Part 9 of this section Do not use fuel of a lower octane rating or automotive fuel regardless of octane rating 2 PRESTARTING ITEMS OF MAINTENANCE Before starting the aircraft engines for the first flight of the day perform the following items of maintenance inspection in conjunction with the aircraft Pilot 5 Operating Handbook preflight check a Be sure all switches are in the Off position b Be sure magneto ground wires are connected c Check oil level 13 SECTION I LYCOMING OPERATION AND INSTALLATION MANUAL OPERATING INSTRUCTIONS L IO 360 M1A d Check fuel level e Check fuel and oil line connections note minor indications for repair at 50 hour inspection Repair any leaks before aircraft is flown f Open the fuel drain to remove any accumulation of water and sediment g Mak
13. EL 360 M1A SERIES COMPRESSION RATIO 8 50 1 SPARK TIMING 25 BTC FUEL INJECTOR PAC TYPE RSA 5AD1 MIXTURE CONTROL MANUAL TO BEST ECONOMY OR BEST POWER AS INDICATED FUEL GRADE MINIMUM 91 96 PERCENT RATED POWER i m MIXTURE SETTING BEST 100 120 140 160 ACTUAL BRAKE HORSEPOWER Figure 3 1 Part Throttle Fuel Consumption 20 SECTION I OPERATING INSTRUCTIONS LYCOMING OPERATION AND INSTALLATION MANUAL L IO 360 M1A 1333 SGNVSNOHL NI SGNLILTV 3 0553 vc EZ CC OZ GE SL L OL SL vi EL eS ULP XENP GL CE GENMD GNND Warm ee MEA EDU MED ZEN NEN Exon nee 33nSS3ud G 103INVN ain losasv 82 2 92 650 vc l 00 6b gl 51 1 1 193HHOO aa3sn Y3LV3H SYNLXIW TVNSH3LX3 ON 0022 d33dS ANIONS 96 16 WNWINIW 30v39 13N4 LAYS YSY OVd 1903 48 Oll vH NOISSSYdWOO VLW 09 Ol 13GON 3NISN3 SASIMYSHLO SSJINN YAMOd WNWIXVAN 3ONVIAHOJMH3d 3NION3 SNIINOOAT1 6vS YAMOd 8 4 gt 4 20 NOILJJYYO9 K131VWIXO3iddV dH IVNL V 1096 AX dH 51 097 WinwWyos Ag S aunivuadWal 5 WOMNJ 1 1 E 3univM3dW3l L3TNI d H 0022 08 30
14. ES L IO 360 M1A This Page Intentionally Left Blank 28 LYCOMING OPERATION AND INSTALLATION MANUAL SECTION II L IO 360 M1A PROCEDURES SECTION II PART 2 PROCEDURES 1 INSTALLING ENGINE a b C Refer to Figures 2 1 through 2 3 for dimensions and connection locations If the engine is to be installed in an airframe from which an engine has previously been removed inspect the engine mounts to ensure they are not bent misaligned distorted or damaged A CAUTION Distorted misaligned bent or damaged engine mounts may cause engine or airframe damage or engine failure Refer to the airframe manufacturer s instructions for attaching the engine to the engine mounts 2 CONNECTING EXTERNAL ACCESSORIES a Refer to installation drawing Figure 2 3 Remove cover plate and gasket When installing the accessory use the gasket and hardware specified by the airframe manufacturer Torque to the value specified for the thread size in the Table of Limits L IO 360 M1A Maintenance and Overhaul Manual Connect oil and fuel supply lines and any reporting devices sensors and senders per the airframe manufacturer s instructions Refer to Figures 2 2 and 2 3 for connection locations Table 2 1 Thread Size Accessory Pad 1 Upper Right Side of 14 20 Accessory Housing Accessory Housing Crankcase 29 SECTION II LYCOMING OPERATION AND INSTALLATION MANUAL PROCEDURES L IO 360 M1A a
15. If preservation oil does contact a painted surface clean it off with a solvent as soon as possible a Remove all the bottom spark plugs 25 SECTION II LYCOMING OPERATION AND INSTALLATION MANUAL PREPARATION L IO 360 M1A b Turn the crankshaft three or four revolutions by hand Tilt the engine to one side until the spark plug holes on that side are oriented vertically Rotate the crankshaft at least two revolutions and allow the oil to drain out through the spark plug holes Repeat steps 3 and 4 for the opposite side of the engine Inspect the spark plugs before reinstalling them If they are not clean wash them in clean oil based solvent Dry them with compressed air g Remove the oil sump plug and allow any preservative oil that has accumulated in the sump to drain Remove the oil screen and clean it with a hydrocarbon based solvent such as Varsol or equivalent Reinstall the oil screen If a constant speed propeller is to be used the expansion plug must be removed from the crankshaft Pierce a 1 8 in to 3 16 in hole in the center of the plug to remove it Replace the oil sump plug and install a safety wire Refer to Maintenance and Overhaul Manual P N LMO L IO 360 M1A for lockwire information Fill the sump with 8 quarts of aviation grade oil Refer to Section I Part 2 for oil recommendations Inspect the induction riser to ensure that it is clean and dry If a significant amount of preservative
16. ONS Model s t EE Serer u L IO 360 M1A BAA Type Certificate a 1E10 Rated HotsepoWwEer uad ade tuts hts Suha 180 RatedspeedeRPMu suu s sanan a p kai a aS ua 2700 CHES sate eho EU Ba de 5 125 4 375 Displacement cubic inches s a a 361 Compression i aus a 8 5 1 Firing ord r Lui aea roten u p ah h 1 3 2 4 Spark occurs desrees B TG ei Muta Dr AAR 25 Valve rocker clearance hydraulic tappets collapsed 028 08 Prop drive tatio a D 1 1 Prop dU vem roldtlon Uu A Clockwise This engine has an alternate rating of 160 HP at 2400 RPM 2 Standard Engine Dry Weight Includes all engine accessories except alternator a 300 Ibs 3 Moments of Inertia Standard Dry Weight all About the axis parallel to the crankshaft centerline 47 58 in lb sec About the vertieal axis Izg sse rer tor ap n
17. UCTIONS NOTE If engine fails to achieve a normal start assume it to be flooded Crank engine over with throttle wide open and ignition off Then repeat above procedure Hot Engine Because fuel percolates the system must be cleared of vapor it is recommended that the same procedure as outlined above be used for starting a hot engine 4 COLD WEATHER STARTING During extreme cold weather it may be necessary to preheat the engine and oil before starting 5 GROUND RUNNING AND WARM UP Subject engines are air pressure cooled and depend on the forward movement of the aircraft to maintain proper cooling Particular care is necessary therefore when operating these engines on the ground To prevent overheating it is recommended that the following precautions be observed NOTE Any ground check that requires full throttle operation must be limited to three minutes or less if indicated cylinder head temperature exceeds the maximum stated in this manual a Head the aircraft into the wind b Leave mixture in Full Rich c Operate the engine on the ground only with the propeller in minimum blade angle setting d Warm up at approximately 1000 1200 RPM Avoid prolonged idling and do not exceed 2200 RPM on the ground e Engine is warm enough for take off when the throttle can be opened without the engine faltering 6 GROUND CHECK a Warm up as directed above b Check both oil pressure and oil temperature c Leave
18. Ute re 70 13 in Ib sec About the axis parallel to the centerline nu 42 41 in Ib sec 4 Accessory Drives Accessory Drive Drive Ratio Direction of Rotation Starter 16 556 1 Counterclockwise Alternator 3 200 1 Clockwise Vacuum Pump 1 300 1 Counterclockwise Hydraulic Pump 1 385 1 Clockwise Tachometer 500 1 Clockwise Propeller Governor 947 1 Clockwise Magneto Drive 1 000 1 Clockwise Fuel Pump 1 000 1 Counterclockwise When applicable Viewed facing drive pad NOTE Engines with the letter L in prefix will have opposite rotation to the above SECTION I LYCOMING OPERATION AND INSTALLATION MANUAL SPECIFICATIONS L IO 360 M1A This Page Intentionally Left Blank 10 LYCOMING OPERATION AND INSTALLATION MANUAL SECTION I L IO 360 M1A OPERATING INSTRUCTIONS SECTION I PART 3 OPERATING INSTRUCTIONS Page General NE RON 13 Prestarting Items of Maintenance 13 Startins Procedures 14 Cold Weather PER a t sasa EE Po poe LE bd equ Uy d Qo eds 15 Ground Running and Warm Up 15 Ground Check qur 15 Operating in Flight
19. aning the mixture observe the following general rules GENERAL LEANING RULES Never exceed the maximum red line cylinder head temperature limit 16 LYCOMING OPERATION AND INSTALLATION MANUAL SECTION I L IO 360 M1A OPERATING INSTRUCTIONS For maximum service life cylinder head temperatures must be maintained below 435 F 224 C during high performance cruise operation and below 400 F 205 C for economy cruise powers On engines with manual mixture control maintain mixture control in Full Rich position for rated take off climb and maximum cruise powers above approximately 75 However during take off from high elevation airport or during climb roughness or loss of power may result from over richness In such a case adjust mixture control only enough to obtain smooth operation not for economy Observe instruments for temperature rise Rough operation due to over rich fuel air mixture is most likely to be encountered at altitudes above 5 000 feet Always return the mixture to full rich before increasing power settings Operate the engine at maximum power mixture for performance cruise powers and at best economy mixture for economy cruise power unless otherwise specified in the airplane owners manual During let down flight operations it may be necessary to manually lean carbureted or fuel injected engines to obtain smooth operation a Leaning to Exhaust Gas Temperature Normally aspirated engines with fuel in
20. ber 1E10 has been issued for this engine The L IO 360 M1A engine has a rated maximum continuous power of 180 hp at 2700 RPM at standard sea level conditions The engine has a bore of 5 125 in a stroke of 4 375 in a piston displacement of 361 cubic inches and a compression ratio of 8 5 1 NOTE The letter L in the model prefix denotes the reverse rotation of the basic model Example model 10 360 has clockwise rotation of the crankshaft Therefore LIO 360 M1A has counterclockwise rotation of the crankshaft Likewise the rotation of the accessory drives of the LIO 360 M1A is opposite those of the basic model as listed in Section I Part 2 of this manual Operational aspects of engines are the same and performance curves and specifications for the basic model will apply Cylinders The nitrided cylinders are air cooled with the major parts head and barrel screwed and shrunk together The heads are made from an aluminum alloy casting with a fully machined combustion chamber Valve guides and valve seats are shrunk into machined recesses in the head Rocker shaft bearing supports are cast integrally with the head along with the housings to form the rocker boxes for both intake and exhaust valve rockers The Lycoming L IO 360 M14A engine incorporates a color coding system painted on the cylinder heads to designate the specific cylinder barrels and spark plugs required The L IO 360 M14A engine has nitrided cylinders indicated
21. e oil system The main bearings connecting rod bearings camshaft bearings valve tappets push rods and crankshaft idle gears are lubricated by means of oil collectors and spray The oil pump which is located in the accessory housing draws oil through a drilled passage leading from the oil suction screen located in the sump The oil from the pump then enters a drilled passage in the accessory housing where a flexible line leads the oil to the external oil cooler In the event that cold oil or an obstruction should restrict the flow of oil to the cooler an oil cooler bypass valve is provided Pressure oil from the cooler returns to a second threaded connection on the accessory housing from which point a drilled passage conducts the oil to the oil pressure screen which is installed in a cast chamber located on the accessory housing below the tachometer drive The oil pressure screen is provided to filter from the oil any solid particles that may have passed through the suction screen in the sump After being filtered in the pressure screen chamber the oil is fed through a drilled passage to the oil relief valve located in the upper right side of the crankcase in the front of the accessory housing This relief valve regulates the engine oil pressure by allowing excessive oil to return to the sump while the balance of the pressure oil is fed to the main oil gallery the oil is distributed by means of separate drilled passages to the main bearings of t
22. e sure all shields and cowling are in place and secure If any are missing or damaged repair or replacement should be made before the aircraft is flown h Check engine controls for general condition travel and freedom of operation i Inspect and service Induction system air filter in accordance with the airframe manufacturer s recommendations 3 STARTING PROCEDURES The following starting procedures are recommended however the starting characteristics of various installations will necessitate some variation from these procedures NOTE Limit cranking periods to ten 10 to twelve 12 seconds with 5 minutes rest between cranking periods a Cold Engine 1 Perform pre flight inspection 2 Set propeller governor in Full RPM 3 Turn fuel valve to on position 4 Turn boost pump on and move mixture control to Full Rich position until a slight but steady flow is indicated 5 Return mixture control to Idle Cut Off position 6 Set magneto selector switch Consult aircraft manufacturer s handbook for correct position 7 Engage starter 8 When engine starts place magneto selector switch in Both position 9 Move mixture control slowly and smoothly to Full Rich 10 Check oil pressure gage for indicated pressure If oil pressure is not indicated within thirty seconds stop the engine and determine trouble 14 LYCOMING OPERATION AND INSTALLATION MANUAL SECTION I L IO 360 M1A OPERATING INSTR
23. em type regulator to convert the air force of the air into a corresponding fuel force This fuel force fuel pressure differential applied across the fuel metering section jet system makes fuel flow proportional to air flow A manual mixture control and idle cut off are provided Particularly good distribution of the fuel air mixture is obtained through the center zone induction system which is integral with the oil sump and is submerged in the oil and aids in cooling the oil in the sump From the riser distribution to each cylinder is by individual intake pipes Fuel vaporization takes place at the intake ports LYCOMING OPERATION AND INSTALLATION MANUAL SECTION I L IO 360 M1A DESCRIPTION Splash Oil to Rocker Arms Valve Stems etc Drain Oil to Sump thru Oil Drain Tubes Rocker Arm Bushings Pro Gravity Oil Thru Shroud Tubes 1 Prop Gov 3 Push Rod 2 a7 Splash Oil to Pistong Piston Pins Cams etc Camshaft Bearing t Use Oil Transfer Cover When Not Using Gov Use Oil Transfer Cover When Not Using Gov Crankpin Splash Oil to Rocker Arms Valve Stems etc Rocker Arm Bushings Drain Oil to Sump thru Oil Drain Tubes A Gravity Oil thru Shroud Tubes Filter O Oil Pump Figure 1 1 Oil System Schematic Diagram Lubrication System The lubrication system is of the pressure wet sump type Figure 1 1 shows a schematic diagram of th
24. h manifold pressure gage may check magneto drop off with engine operating at approximately 2100 2200 RPM 2 Switch from both magnetos to one and note drop off return to both until engine regains speed and switch to the other magneto and note drop off then return to both Drop off must not exceed 175 RPM and must not exceed 50 RPM between magnetos A smooth drop off past normal is usually a sign of a too lean or too rich mixture f Do not operate on a single magneto for too long a period a few seconds is usually sufficient to check drop off and will minimize plug fouling 7 OPERATION IN FLIGHT b See airframe manufacturer s instructions for recommended power settings 8 FUEL MIXTURE LEANING PROCEDURE Improper fuel air mixture during flight is responsible for many engine problems particularly during take off and climb power settings The procedures described in this manual provide proper fuel air mixture when leaning Lycoming engines they have proven to be both economical and practical by eliminating excessive fuel consumption and reducing damaged parts replacement It is therefore recommended that operators of all Lycoming aircraft power plants utilize the instructions in this publication any time the fuel air mixture is adjusted during flight Manual leaning may be monitored by exhaust gas temperature indication fuel flow indication and by observation of engine speed and or airspeed However whatever instruments are used in le
25. he rod journals Oil from the main oil gallery also flows to the cam and the valve gear passages and is then conducted through branch passages to the roller tappets and camshaft bearings Oil enters the tappet through indexing holes and travels out through the hollow push rods to the valve mechanism lubricating the valve rocker bearings and the valve stems Residual oil from the bearings accessory drives and the rocker boxes is returned by gravity to the sump The fuel injection systems control fuel flow in proportion to airflow with injection Dual ignition is furnished by two Slick magnetos and harnesses SECTION I LYCOMING OPERATION AND INSTALLATION MANUAL DESCRIPTION L IO 360 M1A This Page Intentionally Left Blank LYCOMING OPERATION AND INSTALLATION MANUAL SECTION I L IO 360 M1A SPECIFICATIONS SECTIONI PART 2 SPECIFICATIONS Page Specifications C PR 9 Standard Engine Weights svcssceiccccsvsaitacssisseeessdcecscosssiasasccesssesassccdscconsssssassccesseesadescsebaossesasceusdsnconsccessdanasessianes s 9 Moments OF Inertia cM E 9 DIVES OUS 9 SECTION I LYCOMING OPERATION AND INSTALLATION MANUAL SPECIFICATIONS L IO 360 M1A This Page Intentionally Left Blank LYCOMING OPERATION AND INSTALLATION MANUAL SECTION I L IO 360 M1A SPECIFICATIONS SECTION I PART 2 SPECIFICATIONS 1 SPECIFICATI
26. ions and Warnings which must be carefully read in order to minimize the risk of personal injury or the use of improper service methods that may damage the engine or render it unsafe NOTE Read for added information and reminders A CAUTION Equipment damage may result if instructions are not followed WARNING Personal injury could result if instructions are not followed It is also important to understand that these Warnings and Cautions are not all inclusive Lycoming could not possibly know evaluate or advise the service trade of all conceivable ways in which service might be done or of the possible hazardous consequences that may be involved Accordingly anyone who uses a service procedure must first satisfy themselves thoroughly that neither their safety nor aircraft safety will be jeopardized by the service procedure they select ii LYCOMING OPERATION AND INSTALLATION MANUAL L IO 360 M1A SECTIONI PART 1 PART 2 PART3 SECTION II PART 1 PART 2 TABLE OF CONTENTS OPERATION DESCRIPTION SPECIFICATIONS OPERATING INSTRUCTIONS INSTALLATION PREPARATION PROCEDURES Page SECTION L 3 SECTION I 9 SECTION I 13 SECTION II 25 SECTION II 29 iii L IO 360 M1A LYCOMING OPERATION AND INSTALLATION MANUAL This Page Intentionally Left Blank lv LYCOMING OPERATION AND INSTALLATION MANUAL SECTION I L IO 360 M1A DESCRIPTION SECTION I PART 1 DESCRIPTION Page Genepalsu
27. ity in sn 4 U S Qts e Oil Pressure psi Maximum Minimum Idling Start and Warm up Normal Operation 95 55 25 115 f Oil Temperature The maximum permissible oil temperature is 245 F 118 C For maximum engine life maintain desired oil temperature between 165 F 73 8 C and 200 F 93 3 C in level flight cruise conditions g Fuel and Oil Consumption Fuel Max Max Cons Oil Cons Cyl Head Operation RPM HP Gal Hr Qts Hr Temp Normal Rated 2700 180 80 500 260 Performance Cruise 75 Rated 2450 135 11 0 45 500 260 Economy Cruise 60R Rated 2350 117 8 5 39 500 F 260 C At Bayonet Location For maximum service life of the engine maintain cylinder head temperatures between 150 and 400 F during continuous operation This engine has an alternate rating of 160 HP at 2400 RPM 18 LYCOMING OPERATION AND INSTALLATION MANUAL SECTION I L IO 360 M1A OPERATING INSTRUCTIONS 10 ENGINE SHUT DOWN a Set propeller at minimum blade angle b Idle until there is a decided decrease in cylinder head temperature c Move mixture control to Idle Cut Off d When engine stops turn ignition switch off 19 SECTION I LYCOMING OPERATION AND INSTALLATION MANUAL OPERATING INSTRUCTIONS L IO 360 M1A FUEL CONSUMPTION LB CURVE NO 12849 A PART THROTTLE FUEL CONSUMPTION LYCOMING ENGINE MOD
28. jectors or carburetors 1 Maximum Power Cruise approximately 75 power Never lean beyond 150 F on rich side of peak EGT unless aircraft operator s manual shows otherwise Monitor cylinder head temperatures 2 Best Economy Cruise approximately 7596 power and below Operate at peak EGT b Leaning to Flowmeter Lean to applicable fuel flow tables or lean to indicator marked for correct fuel flow for each power setting 9 ENGINE FLIGHT CHART a Fuel Requirements 91 96 or 100LL Octane Minimum Aviation Grade Fuel b Fuel Pressure psi Min Max Inlet to fuel pump 2 35 Inlet to fuel injector 14 45 17 SECTION I LYCOMING OPERATION AND INSTALLATION MANUAL OPERATING INSTRUCTIONS L IO 360 M1A c Oil Requirements Recommended Grade Oil MIL L 22851 or MIL L 6082B or SAEJ1899 Spec Average SAEJ1966 Spec Ashless Dispersant Ambient Air Mineral Grades Grades All Temperatures SAEI5W50 SAE20W 50 Above 80 F SAE60 SAE60 Above 60 F 5 50 SAE40 SAESO 30 F to 90 F SAE40 SAE40 O F to 70 F SAE30 SAE40 SAE30 SAE20W40 Below 10 F SAE20 SAE30 or SAE20W30 In new newly overhauled or rebuilt engines or following the replacement of one or more cylinders use only mineral oil during the first 50 hours of operation d Oil Sump Capacity EMCIESBUSNDLA AD haste in 8 U S Minimum safe quant
29. rocedures are contained in the Lycoming Maintenance and Overhaul Manual maintenance personnel must refer to these for such procedures SAFETY WARNING MAINTENANCE MUST BE PERFORMED BY QUALIFIED AND PROPERLY CERTIFIED PERSONNEL NEGLECTING TO FOLLOW THE OPERATING INSTRUCTIONS AND TO CARRY OUT PERIODIC MAINTENANCE PROCEDURES CAN RESULT IN POOR ENGINE PERFORMANCE AND POWER LOSS ALSO IF POWER AND SPEED LIMITATIONS SPECIFIED IN THIS MANUAL ARE EXCEEDED FOR ANY REASON DAMAGE TO THE ENGINE AND PERSONAL INJURY CAN HAPPEN CONSULT YOUR LOCAL FAA APPROVED MAINTENANCE FACILITY SERVICE PUBLICATIONS Lycoming service publications and subscriptions are available through Lycoming distributors or direct from the factory NOTE The illustrations pictures and drawings shown in this publication are typical of the subject matter they portray in no instance are they to be interpreted as examples of any specific engine equipment or part thereof L IO 360 M1A LYCOMING OPERATION AND INSTALLATION MANUAL IMPORTANT SAFETY NOTICE Proper service and repair is essential to increase the safe reliable operation of all aircraft engines The service procedures recommended by Lycoming are effective methods for performing service operations Some of these service operations require the use of tools specially designed for the task These special tools must be used when and as recommended It is important to note that this manual uses the following Notes Caut
30. starter to cool after each energizing period Refer to the starter manufacturer s instruction manual for additional information NOTE If oil pressure is not determined after the first cranking of 10 to 15 seconds allow the starter to cool and repeat the cranking starter cooling sequence until 20 lb is indicated on the oil pressure gage or oil flow is observed A CAUTION If there is no indication of steady oil pressure after five attempts the cause should be determined and fixed 33 SECTION II LYCOMING OPERATION AND INSTALLATION MANUAL PROCEDURES L IO 360 M1A L g Turn the starter for an additional 10 seconds to verify that the oil pressure remains at latest 20 Ib Reinstall the spark plugs and proceed with normal starting procedures immediately Refer to Section I Part 3 When the engine starts observe the oil pressure gage If there is no oil pressure indication shut down the engine until cause is determined Allow the engine to run for approximately 3 minutes at 1000 rpm Shut down in accordance with Section I Part 3 Step 10 34
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