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Installation & Operation Manual

1. Figure 5 O 360 Installation Drawing Top View 6 Appendix A O 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data enone SC O 360 Series Engine FUEL INLET 250 18NPSF 2 38 FUEL PRESSURE CONNECTION _ 125 27NPSF 5N m 2 72 1 50 rog ME R1 75 IDLE CUT OFF lt Z FULL RICH X 76 309 255 250DIA RADIAL CLEARANCE MUST BE MAINTAINED AS SHOWN AT FULL P P d RICH POSITION OF LEVER 2 296 7 R42 472 2 136 pa 162 ce 3 30 Z m W ALLOWABLE LINEAR TRAVEL i 4 26 R1 69 2 70 188 187 DIA 1 LK ok THROTTLE THROTTLE CLOSED lt OPEN 89 REF a KZ L CH K 250 18 NPSF Fuel Metering System Carburetor Figure 6 Carburetor Installation Drawing 7 March 2004 Superior Air Parts Inc p Engine Appendix A O 360 Model Specification Data SUPERIZR Model Specification Data Vintage Engine oe Nes O 360 Series Engine Propeller Load and Full Throttle Curves Superior Vantage O 360 Series Full Rich 9 e es eee es ee EF I ad eee E ee ue e ep eee a oe ee ee e 2 e Absolute Dry Manifold Pressure 7
2. 0 5000 10000 15000 20000 25000 Frequency Hz Figure 3 8 Engine Mount Forcing Function for Engine Startup and Shutdown Engine Forcing Functions on Firewall Steady State Operation Superior Vantage O IO 360 L Toson 1 22 LE 222 2 LT aaa Ey Bending Hofizental Pp jee Er gi epee Pee eee eee eee ER EE J Bending Vertical SE 1 1 al I E I I iH I T I 4 I i I i I I I I I I i I i I I I I I I I I I I I I I I I I I I I I I I I 0 5000 10000 15000 20000 25000 Frequency Hz Figure 3 9 Engine Mount Forcing Function for Steady State Conditions 27 Chapter 3 Aircraft Engine March 2004 Superior Air Parts Inc Integration Considerations SUPERIZR R P Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i antage Engine CHAPTER 4 Engine Installation 1 GENERAL INSTRUCTIONS Superior Vantage Engines are carefully packaged to prevent shipping damage and preserved for extended storage These measures include the use of metal shipping fixtures isolation mounts and desiccant plugs when preserved for extended storage These items are not intended for further use and should be discarded when the engine is unpacked Superior Air Parts recommends particular attention to the discard of hardware used to secure the engine during shipment and in the a
3. 27 antage Engine O 360 amp 10 360 SERIES ENGINES INSTALLATION amp OPERATION MANUAL S GI J ay Ir m m E D m j ec T SE 621 South Royal Lane Suite 100 Coppell TX 75019 800 277 5168 www superior air parts com P N SVIOMO1 Revision A March 2004 FAA Approved SUPERIZR Installation amp Operation Manual Waaa Engine O 360 and 10 360 Series Engines DISCLAIMER OF WARRANTIES AND LIMITATIONS OF LIABILITY SUPERIOR S EXPRESS WARRANTIES AND THE REMEDIES THEREUNDER ARE EXCLUSIVE AND GIVEN IN PLACE OF A ALL OTHER WARRANTIES EXPRESS IMPLIED OR STATUTORY WHETHER WRITTEN OR ORAL INCLUDING BUT NOT LIMITED TO ANY WARRANTY OF MERCHANTABILITY FITNESS OR PARTICULAR PURPOSE OR IMPLIED WARRANTY ARISING FROM PERFORMANCE COURSE OF DEALING OR USAGE OF TRADE AND B ALL OTHER OBLIGATIONS LIABILITIES RIGHTS CLAIMS OR REMEDIES EXPRESS OR IMPLIED ARISING BY LAW OR OTHERWISE INCLUDING BUT NOT LIMITED TO ANY RIGHT OR REMEDIES IN CONTRACT TORT STRICT LIABILITY OR ARISING FROM SUPERIOR S NEGLIGENCE ACTUAL OR IMPUTED SUPERIOR S OBLIGATIONS AND PURCHASER S REMEDIES UNDER SUPERIOR S EXPRESS WARRANTIES ARE LIMITED TO SUPERIOR S CHOICE OF REFUND REPAIR OR REPLACEMENT ON AN EXCHANGE BASIS AND EXCLUDE LIABILITY FOR INCIDENTAL SPECIAL CONSEQUENTIAL OR ANY OTHER DAMAGES INCLUDING WITHOUT LIMITATION ANY LIABILITY OF CUSTOMER TO A THIRD PARTY OR FOR ECONOMIC LOSS REPLACEMENT COST
4. ferot EE Below Peak EGT EE Baa ES SES SE 7 c pee EF FF FFF ee nsrc utp SEE lie Len EC ER ae ee 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 72 74 Fuel Flow Lb Hr Figure 13 Fuel Mixture Curve 65 Power 14 Appendix B 10 360 Model March 2004 Superior Air Parts Inc Specification Data AIR PART SUPERIZR Model Specification Data k PE hi 10 360 Series Engine Minimum Oil Quantity Superior Vantage O 10 360 Series 3 5 Oil Quantity U S Quarts 1 0 5 0 30 20 10 0 10 20 30 Engi Enoi ER Roll Angle Deg Right Figure 14 Minimum Oil Quantity 15 Appendix B 10 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data Tia Engine oe 10 360 Series Engine Table 1 Maximum Fuel Flow Requirements Max Rich Fuel Flow Required Pounds Per Hour 10 360 108 Table 2 Fuel Filter Requirements 100 Mesh Screen 0 005 Max Particle Size Table 3 Fuel Pump Inlet Pressure Limits Minimum PSIG Maximum PSIG 10 360 2 0 35 0 Table 4 Oil Heat Rejection Airside Heat Rejection Crankcase Pressure ee Typical 1 450 BTU Minute Oil Heat R t GE Maximum 2 1000 BTU Minute w 1800 Ft Min Sea Level Minimum Cylinder Cooling Airflow Drop Recommended Im ealach 6 5 In H20 Baffle Press Drop Crankcase Pressure Maximum 4 0 In H O Notes 1 Typical Heat Rejection In Cruise 2 Maximum Heat Re
5. c o i Installation amp Operation Manual O 360 and IO 360 Series Engines N27 i anlage Engine 4 ENGINE NOT ABLE TO DEVELOP FULL POWER Table 7 4 Engine Not Able To Develop Full Power Probable Cause Leak in the injection system Throttle lever out of adjustment Improper fuel flow Restriction in air scoop Improper fuel Faulty ignition 5 ROUGH ENGINE OPERATION Correction Tighten all connections and replace damaged parts Adjust throttle lever Check strainer gage and flow at the fuel inlet Examine air scoop and remove restrictions Drain and refill tank with proper fuel Tighten all connections Check system with tester Check ignition timing Table 7 5 Rough Engine Operation Probable Cause Broken engine mount Mounting bushings worn Unstable compression 6 LOW POWER amp ENGINE RUNS ROUGH Correction Replace or repair mount Install new mounting bushings Check compression Table 7 6 Low Power amp Engine Runs Rough Probable Cause Mixture too rich indicated by sluggish engine operation red exhaust flame at night Extreme cases indicated by black smoke from exhaust Mixture too lean indicated by overheating or back firing Leaks in induction system Defective spark plugs Improper fuel Magneto breaker points not working properly Defective ignition wire Defective spark plug terminal connectors March 2004 Superior Air Parts Inc Correction Readjustment of fuel in
6. A manual primer system is provided on all engines using a carburetor Fuel injected engines do not require a manual priming system relying instead on the fuel injectors for priming Ignition System Dual ignition is furnished by two Unison magnetos with two spark plugs per cylinder Each magneto is equipped with impulse coupling for improved starting Chapter 1 Engine Description UPERIZR R PARTS Installation amp Operation Manual O 360 and 10 360 Series Engines N2Z anlage Engine CHAPTER 2 Airworthiness Limitations The Airworthiness Limitations Section is F A A approved and specifies maintenance required under sections 43 16 and 91 403 of the Federal Aviation Regulations unless an alternate program has been FAA approved This section is part of the type design of the O 360 and lO 360 engine series pursuant to certification requirements of the Federal Aviation Regulations 1 MANDATORY REPLACEMENT TIME Subject to additional information contained in F A A Approved Mandatory Service Bulletins issued after the date of certification the O 360 and 10 360 engine series do not contain any components having mandatory replacement times required for type certification 2 MANDATORY INSPECTION INTERVALS Subject to additional information contained in F A A Approved Mandatory Service Bulletins issued after the date of certification the O 360 and 10 360 engine series do not contain any components having mandator
7. Engine Torque Maneuvering Moment Ultimate g Load Engine Torque Maneuvering Moment Load Limit Positive Negative 4361 Ft Lb 2181 Ft Lb 1634 Ft Lb 1634 Ft Lb 6542 Ft Lb 3271 Ft Lb 2451 Ft Lb 2451 Ft Lb Note Positive maneuvering moment values result in a downward force on the engine and negative values result in an upward force March 2004 Superior Air Parts Inc 25 Chapter 3 Aircraft Engine Integration Considerations SUPERIZR R PARTIS Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i anlage Engine 6000 4000 2000 2000 4000 Vertical Force Lbf 6000 8000 10000 8 00 8 50 9 00 9 50 10 00 10 50 Longitudinal C G Location In 11 00 11 50 12 00 Note The location of the center of gravity in Figure 3 7 is based from the crankcase backplane and can be modified to describe the mounting gage point specific to a given mount style as described in Figures 3 4 through 3 6 above Figure 3 7 Limit and Ultimate Engine Forces D Engine Mount Vibration The use of isolators in the design of the engine mount reduces the magnitude of vibratory loads and Superior has designed the Vantage Engine for state of the art isolation systems However no isolation system is perfect and some loads are transmitted from the engine propeller system to the airframe Itis important during the installation design to
8. PREVENT INJURIES TO PERSONNEL AND OR DAMAGE TO THE EQUIPMENT A Prior to Break In Start Up 1 Engine oil sump should be filled with 100 straight weight mineral oil Use MIL L 6082 grade 100 Refer to chapter seven for fluid requirements 2 Engine must be pre oiled and oil pressure obtained prior to start up a To pre oil an engine do the following i Attach pressure oiling equipment to one end of the main gallery and force appropriate type of oil through the gallery at 35 psi until oil flows from the opposite gallery with the plug removed from the front end of the opposite galley ii Engine baffles and seals must be in good condition and properly installed iii Verify accuracy of instruments required for engine operation CAUTION BREAK IN OF AN ENGINE IN FRIGID CONDITIONS CAN LEAD TO CYLINDER GLAZING AND FAILED BREAK IN DUE TO LOW OIL TEMPERATURE IT IS RECOMMENDED THAT OIL TEMPERATURE BE MAINTAINED BETWEEN 180 AND 190 F Chapter 5 Special Procedures SUPERIZR R PARTIS B Break In Ground Run 1 Flight propeller may be used if test club is not available 2 Head aircraft into the wind 3 Start engine and observe oil pressure Oil pressure should be indicated within 30 seconds If this does not occur shut down engine and determine cause 4 Run engine just long enough to confirm all components are properly adjusted and secured There must be no fuel and or oil leaks 5
9. a nehae of Mercury moe ga ee 23 22 21 20 iQ E ECERERMLLLLLCECCECCE i me E im SERRE PRES T SEE W Se See k E j e L E 130 J Es in Brake Horsepower SSES ES EE gae EE ceci ag sss DEE EE iat rs Sas sss en k aep u in 0 70 0 65 pet I Brake SES 0 60 Fuel Consumption miii Hr 0 50 1900 2000 2100 2200 2300 2400 2500 2600 2700 2800 RPM Figure 7 Propeller Load And Full Throttle Curves 8 Appendix A O 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data Vice or RE O 360 Series Engine Altitude Performance Superior Vantage O IO 360 Series Std Alt Temp Best Power Example Flying at 25 1 MP 2400 RPM 2200 ft and at 75 F outside Jair temp the engine should produce 139 Hp on a standard day HPs However the inlet air is 25 F higher than standard day 75 F vs 50 JF so we must correct for this by multiplying HPs by the square root of the temperature ratio adjusting for absolute or Rankine temperature Thus 139x 460 50 460 75 0 5 135 7 HP actual EE eg n M 24 S po p eR s n PE Sea Level Performance LevelPerformance Limiting manifold Koss Le I EE EE EF E Pressure Altitude Ft x 1000 Absolute Dry Manifold Pressure In Hg eee EE Ed See EES ES SE EE eg DE ZA
10. system heat 4 Exhaust System Support The exhaust system should be supported in such a way as to prevent vibration and thermal growth from imparting stress on the pipes The exhaust system should be hard mounted to the cylinder head using the studs provided at the exhaust port and should have flexible mounts at or near the exit Interim supports if needed should be of a flexible style 5 Joint Design The exhaust system should be designed for ease of installation and also to provide flexibility for thermal growth during operation Multiple piece exhaust systems are preferable to single piece designs for both of these reasons Care should be given to the location of slip joints in the exhaust system so that their placement does not interfere with preferred locations for cabin heat muffs and also to provide for thermal growth between hot and cold sections For example large sections that are welded together without slip joints to allow for thermal variations can cause stresses in the system that can lead to early failure The number of welded and slip joints should be minimized to limit the potential for exhaust leaks Also welds should be of superior quality to prevent metallurgical or fatigue failure and subsequent exhaust leaks Chapter 3 Aircraft Engine Integration Considerations SUPERIZ A R PART NC 6 EGT Probes Exhaust gas temperature EGT probes are commonly added to engine installations to prov
11. 10 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data Vi ge score e 10 360 Series Engine 1935 AS DIA J CN 7 Z f y e MIXTURE CONTROL N VALVE CLOSED 80 Fuel Metering System Fuel Injector Figure 6 Fuel Injection Installation Drawing 7 Appendix B 10 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data Vintage Engine RE 10 360 Series Engine Propeller Load and Full Throttle Curves Superior Vantage 10 360 Series Full Rich Absolute Dry Manifold Pressure IIoISIIIGI S i K DE Inches of Mercury eje po ees a EE ee pee Em EE coule E Full Throttl e E e 0 60 i Brake Specific Fa Fuel Consumption Lb Hp Hr Ee 0 55 Full 0 50 ES 1900 2000 2100 2200 2300 2400 2500 2600 2700 2800 RPM Figure 7 Propeller Load And Full Throttle Curves 8 Appendix B 10 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data Vice or RE 10 360 Series Engine Altitude Performance Superior Vantage O IO 360 Series Std Alt Temp Best Power Example Flying at 25 1 MP 2400 RPM 2200 ft and at 75 F outside Jair temp the engine should produce 139 Hp on a standard day HPs However the inlet air is 25 F higher than standard day 75 F vs 50 JF so we must correct for this by mu
12. 2004 Superior Air Parts Inc Chapter 1 Engine Description SUPERIZ Installation amp Operation Manual rr Wk O 360 and 10 360 Series Engines INTER CYLINDER BAFFLE B W seu E Im H ae Ld m ime EUNT HII W III Li pi OI EE HU ll MAGNETO OIL FILTER Figure 1 4 O 360 Engine Top View N27 i antage Engine MAGNETO March 2004 Superior Air Parts Inc Chapter 1 Engine Description SUPERIZR Installation amp Operation Manual Sanne Engine WED ash O 360 and 10 360 Series Engines OIL TEMP CONNECTION EYE TACHOMETER CONNECTION ALTERNATE OIL TO COOLER BRACKET OIL RETURN FROM COOLER BREATHER VACUUM PUMP ACCESSORY PAD FITTING OIL PRESSURE GAGE CONNECTION OIL FILTER OIL LEVEL TUBE amp GAGE N Yp 7 Os 2 Le J he ie asd SS a mr eb L PRESSURE e d lig Ee D CONNECTION D Lu T D hose S ST SK ae T NN LS GROUND OR P LEAD TERMINAL GROUND OR P LEAD TERMINAL OIL SUPPLY TO COOLER VENT LINE nD Jig OIL LINE TO CONNECTION e LAA PROPELLER DIAPHRAGM FUEL PUMP OIL DRAIN PLUG COMMON PRIMER G LINE SOURCE FUEL PUMP INLET FUEL LINE OIL SUCTION SCREEN FUEL MIXTURE THROTTLE LEVER LEVER Figure 1 5 O 360 Engine Rear View March 2004 Superior Air Parts Inc Chapter 1 Engine Description SUPERIZ Installation amp Operation Manual Zntage Engine WE O 360 and 10 360 Series Engines FU
13. 3 Aircraft Engine Integration Considerations SUPERIZR R PARTIS Specification Data the valve may be adjusted as follows With the engine warmed up and running at 2000 RPM observe the oil pressure gage reading If the pressure is above maximum or below minimum specified limits stop the engine and turn the adjusting screw with either a flathead screwdriver or a 9 16 inch box wrench inward clockwise to increase pressure or outward counter clockwise to decrease pressure See Table 5 of the Model Specification Data for specific oil pressure data 3 Vernatherm and Oil Cooler Automatic oil temperature control valves Vernatherm valves are used to govern the flow of oil through the external oil cooler These valves are set at the time of assembly and are not serviceable by the operator When the engine is cool the vernatherm valve is open and oil is free to flow directly through the engine without being routed through the external oil cooler As the oil temperature reaches its desired limits however some or all of the oil is routed through the oil cooler circuit The oil cooler circuit is the only part of the lubrication circuit that is controlled by the installation design It is necessary to maintain good hydraulic practices in the design of the oil cooler circuit to minimize flow and pressure losses These include using large diameter hoses and avoiding sharp bends and restrictive couplings whenever possible Flow an
14. BREATHER FITTING FUEL INJECTION MANIFOLD EYE OIL PRESSURE GAGE CONNECTION BRACKET OIL RETURN FROM COOLER r OIL LEVEL TUBE amp GAGE an OIL FILTER cl 9 D A aM m lt lt 1 SC Ae yd ANT E A SE mte S VW all WH M W LEM a E MANIFOLD MT TT lt PRESSURE CONNECTION t 1 Me Yi TT AL a B9 m e GROUND OR P LEAD TERMINAL A VI p 7 OIL SUPPLY TO COOLER GROUND OR P LEAD TERMINAL j Pa OIL LINE TO EX H PROPELLER EN FUEL PUMP INLET Lat G il DIAPHRAGM FUEL _ OIL DRAIN PLUG PUMP Tp P OIL SUCTION SCREEN OIL DRAIN PLUG TH RATE ee FE VENT UNE CONNECTION MIXTURE CONTROL LEVER Figure 1 9 10 360 Engine Rear View 12 March 2004 Superior Air Parts Inc Chapter 1 Engine Description A S 5 FEATURES AND OPERATING MECHANISMS Crankshaft The crankshaft is made from aerospace grade SAE 4340 Vacuum Arc Remelt V A R steel per AMS 6414 All bearing journal surfaces are nitrided Connecting Rods The connecting rods are made from aerospace grade SAE 8740 forgings per AMS 6325 They have replaceable bearing inserts in the crankshaft ends and bronze bushings in the piston ends The bearing caps on the crankshaft ends are retained by two bolts with self locking nuts per cap Caps are tongue and groove type for improved alignment and rigidity Camshaft Valve Operating Mechanism The camshaft is located above a
15. COST OF CAPITAL LOST REVENUE LOST PROFITS OR LOSS OF USE OF OR DAMAGE TO AN AIRCRAFT ENGINE COMPONENT OR OTHER PROPERTY AND IN NO EVENT WILL SUPERIOR S LIABILITY EXCEED THE ORIGINAL COST OF THE ENGINE OR ACCESSORY Written notice of any warranty claim must be submitted to Superior within thirty 30 days of a suspected defect in material or workmanship and the engine accessory or part must be made available for Superior s inspection within thirty 30 days after the claim has been made Superior reserves the right to deny any claim not submitted in accordance with these requirements These LIMITED WARRANTIES are the only warranties offered by Superior No agreement varying these warranties or Superior s obligations under them will be binding on Superior unless made in writing by a duly authorized representative of Superior Superior will not process or honor warranty claims on delinquent accounts March 2004 Superior Air Parts Inc EIE aci Chapter 1 Chapter 2 Chapter 3 Chapter 4 Chapter 5 Chapter 6 Installation amp Operation Manual O 360 and 10 360 Series Engines Table Of Contents Revision History List Of Figures List Of Tables Introduction About This Manual Related Publications Installation Approval Requirements Obtaining Service Information Engine Description General Description Continued Airworthiness Model Designations Engine Components General Description Features And Operating Mechanisms O
16. Figure 3a Location of Engine Center of Gravity Horizontal 3 Appendix A O 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data risa iaie i O 360 Series Engine lig J SS gt di des Zi B LES z E LIN HE BE COMMA y d lt nim V ERU 7 ONE GH gt Figure 3b Location of Engine Center of Gravity Vertical 4 Appendix A O 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data ga ur ee REF O 360 Series Engine Figure 4 O 360 Installation Drawing Front View 5 Appendix A O 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data Seria taine TUS O 360 Series Engine m mim WI al
17. Inc Specification Data SUPERIZR Model Specification Data jie PP s e 10 360 Series Engine Figure 4 10 360 Installation Drawing Front View 5 Appendix B 10 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data ia garg UT 10 360 Series Engine Figure 5 10 360 Installation Drawing Top View 6 Appendix B
18. Install cowling 6 Operate engine at 1000 1200 RPM until oil has reached minimum operating temperature 120 7 Check magneto drop at normal RPM 8 If engine is equipped with a controllable pitch propeller cycle only to a 100 RPM drop 9 Shut down engine and check for fuel and or oil leaks and repair any discrepancies 10 At no time should cylinder head temperature be allowed to exceed recommended maximum cruise limit of 430 F C Break In Flight Operation 1 Perform normal pre flight and run up in accordance with Chapter 6 Section 3 remember cycle controllable pitch prop to only a 100 RPM drop Keep ground runs to a minimum 2 Conduct normal take off at full power full rich mixture to a safe altitude Note In certain geographic locations and weather conditions eg high density altitudes Full Rich operation may not be practical In this event substitute the reguirement of Full Rich as discussed in this chapter with the richest practical setting March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and IO 360 Series Engines N27 i antage Engine 3 Lean fuel mixture and maintain shallow climb Use caution to not overheat the cylinders Should overheating occur reduce power and or enrichen mixture 4 Monitor RPM oil pressure oil temperature and cylinder temperature 5 During the first hour of operation maintain level flight
19. March 2004 Superior Air Parts Inc Installation Approval Requirements The engine warranty for a Vantage Engine installation is subject to the technical approval of Superior Upon approval of an installation design Superior will provide a letter that states in part that the installation design is acceptable and does not adversely effect the function of the engine with respect to engine longevity while the engine is operated in accordance with recommended procedures Superior requires certain technical data regarding the installation in order to determine its acceptability for warranty purposes This data may include but is not limited to drawings photographs and test data Approval of the installation for these purposes is limited to the installation design furnished by the airframe manufacturer to Superior Modifications or changes to the installation design requires a new or amended letter of approval prior to the warranty becoming effective for that design Approval of the installation by Superior as described above is limited to engine warranty issues only It does not in any way indicate approval of other aspects of the installation design such as structural integrity and manufacturability Superior Vantage Engines discussed in this document must be installed and operated in accordance with the limitations conditions and Operating procedures described in this document the Model Specification Data and the Installation and
20. Operating Conditions Max Oil e Fuel Cons Max Cyl Operation RPM MAP HP Cons Lbs Hr Qts Hr Head Temp 108 e Maximum Rated 2700 WOT 180 Best Pwr 75 500 F Performance 72 Cruise 8096 2500 26 144 Best Pwr 50 500 F Rated Economy Cruise e 52 2 60 Rated 2400 24 108 Peak EGT A0 500 F Table 12 Accessory Temperature Limits Magnetos 185 F Ambient Starter None Fuel Pump See Chapter 6 Operating Instructions for Fuel Temp Limits 18 Appendix B 10 360 Model March 2004 Superior Air Parts Inc Specification Data
21. Operation Manual O 360 and 10 360 Series Engines 10 WZ i anlage Engine 8 If equipped with a carburetor air temperature gage partial heat may be used to keep the mixture temperature above freezing Constant high temperatures are to be avoided because of a loss in power and variation of mixture High intake air temperatures also favor detonation and pre ignition both of which are to be avoided if normal service life is to be expected from the engine CAUTION USE CAUTION WHEN OPERATING WITH PARTIAL CARBURETOR HEAT ON AIRCRAFT THAT DO NOT HAVE A CARBURETOR AIR TEMPERATURE GAGE IT IS RECOMMENDED TO USE EITHER FULL HEAT OR NO HEAT IN AIRCRAFT THAT ARE NOT SO EQUIPPED 9 Approach and Landing Note During a landing approach the carburetor heat should normally be in the Hot or Full On position If full power is required under these conditions as for an aborted landing the carburetor heat should be returned to the Cold or Off position as full power is applied Under certain hot and dry ambient conditions carburetor heat may not be required See the aircraft flight manual for specific instructions Chapter 6 Normal Operating Procedures E l Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i anlage Engine CHAPTER 7 Abnormal Operating Procedures Table 7 1 Abnormal Operating Procedures 1 GENERAL This section provides the Fault Isolation procedures as a guid
22. Power Hp Figure 8 Altitude Performance At Best Power 9 Appendix A O 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data Visage RE O 360 Series Engine Cruise Performance Superior Vantage O IO 360 Series 8096 Power 144 Hp Rich of Peak Operation s EE EE No ne 2200 rt LL Motor Gasoline UNO FEN B 430 F CHT MIT LS lyr Lp 30 N e N o a ERR E ee E GE Sch gt N NI No with Motor Gasoline Above 500 F CHT BG SC e 6 58 60 62 64 66 6 8 70 72 74 76 78 94 Fuel Flow Lb Hr N o Absolute Dry Manifold Pressure In Hg N o 24 5 Figure 9 Cruise Performance Map 80 Power 10 Appendix A O 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data a RE O 360 Series Engine Cruise Performance Superior Vantage O IO 360 Series 7096 Power 126 Hp Rich of Peak Operation 30 29 N N N N N A o o N o Absolute Dry Manifold Pressure In Hg N o 21 50 84 Fuel Flow Lb Hr Figure 10 Cruise Performance Map 70 Power 11 Appendix A O 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data k EN Engine O 360 Series Engine Cruise Performance Superior Vantage O IO 360 Series 60 Power 108 Hp Rich of Peak Operation 28 27 26 Absolute Dry Manifold Pressur
23. Whenever possible collector elements should be avoided due to their potential to reduce engine performance If necessary collectors should be designed to eliminate the potential for acoustic pressure waves to be reflected back through the exhaust system This may include features internal to the collector such as damping plates perforated pipes etc Such features necessarily increase flow losses through the system and therefore increase exhaust backpressure and care should be taken to minimize this problem Also abrupt increases or decreases in piping size such as in a collector can increase flow losses and should be avoided March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and 10 360 Series Engines 10 N27 i anlage Engine 3 Shrouds and Thermal Protection Exhaust gas temperatures can be as high as 1600 F Therefore it is sometimes necessary to shield thermally sensitive components Control cables hoses engine isolator components nose gear tires etc should be either located far enough from the exhaust pipes to not be damaged by the heat insulated or shielded Fuel lines should be insulated as appropriate to prevent safety concerns or vaporization of the fuel within the lines Similar care should be given to oil or hydraulic lines Also intake air system components including carburetors and fuel injector servo bodies should be shielded either by distance or material from exhaust
24. at 75 power Vary the power setting every 15 minutes during the second hour between 65 75 6 Avoid long descents at cruise RPM and low manifold pressure could cause ring flutter 7 Continue flying at 65 75 power and full rich mixture on subsequent flights while monitoring RPM Oil Pressure Oil Temperature Cylinder Head Temperature and oil consumption Continue until oil consumption stabilizes and cylinder head temperatures drop and stabilize These are indications that the piston rings have seated and the cylinders are broken in 8 At no time should cylinder head temperature be allowed to exceed recommended maximum cruise limit 430 F 9 After landing check again for any fuel and or oil leaks or other discrepancies and repair D Post Break In Procedures 1 After break in drain all mineral oil Examine this oil for foreign matter or metal particle content 2 Install ashless dispersant of the appropriate grade for the expected normal operating conditions and ambient temperature Chapter 5 Special Procedures SUPERIZR R P 4 GENERAL INSPECTION CHECK Perform periodic Inspection Check procedures Refer to Inspection Check section of the Vantage Maintenance Manual for Periodic Inspections intervals NOTE The following inspection does not constitute a complete aircraft inspection It applies to the engine only Refer to the airframe manufacturer s instructions for additional informa
25. cooling airflow over the cylinders and barrels In addition the installation design must include baffles that attach to the engine and provide a seal to the interior of the cowl thus creating a separation between the upper and lower cowl volumes This is typically done primarily with metal components for stiffness against the ram air pressure with flexible rubber seals to conform to the contours of the upper cowl and to allow for relative movement between the engine and cowl March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i anlage Engine The lubricating oil for Superior Vantage Engines must be cooled by means of an air to fluid heat exchanger Typically this heat exchanger is mounted to the engine mount structure and fastened to a rear engine baffle s open to the upper plenum and facing the nose of the cowl In this way ram effect of the cooling air entering the upper plenum can be utilized to increase the airflow through the heat exchanger B Airside Heat Rejection Airside heat rejection that is heat rejected through the cylinder heads barrels and crankcase etc is a primary means for cooling the engine The resulting temperature of the engine is in direct proportion to the amount and quality of cooling air that passes over the engine The engine cowl baffles create an upper plenum fed by incoming air from the front of the cowl that in turn provides cooli
26. enhancing performance of the engine Regardless of the style employed several factors should be considered to make an effective exhaust system Chapter 3 Aircraft Engine Integration Considerations SUPERIZR R PARTIS 1 Exhaust Pipe Exits Exhaust exits should be positioned such that the gasses are released clear of the aircraft and not allowed to reenter the cabin Also the exhaust exits should be located far enough away from the aircraft structure to prevent corrosive byproducts of combustion from causing damage Enlarged exit pipes can be used to change the tone and volume of the exhaust sound Care should be taken however not to enlarge the exit pipes so much as to create sound amplification as with a megaphone 2 Limit Backpressure As discussed earlier high exhaust backpressure can have detrimental effects on engine performance Other than acoustic pressure wave effects backpressure can be minimized in the design by good piping design practices to limit flow losses For example exhaust pipe size should be kept as large as practicable and never less than the exhaust port size Exhaust pipe lengths other than being equal for tuning purposes should be as short as practicable Bends should be large radius smooth and as few as possible Pipe intersections should be at acute angles whenever possible and never at large angles where acoustic waves might be oriented backward up an adjoining pipe
27. or obstruction Fill to proper level with specified oil Replace with oil conforming to specifications Remove and clean oil strainers Check condition of engine rings Replace if worn or damaged Examine sump for metal particles If found engine overhaul may be required Replace gage Table 7 9 Excessive Oil Consumption Probable Cause Low grade of oil Failing or failed bearings Worn piston rings Incorrect installation of piston rings Failure of rings to seat on new cylinders March 2004 Superior Air Parts Inc Correction Fill tank with oil of proper weight and grade Check sump oil for metal particles Install new rings Install new rings Use mineral base oil Climb to cruise altitude at full power and operate at 7596 cruise power setting until oil consumption stabilizes See Break In Procedures Special Procedures Section Chapter 5 Chapter 7 Abnormal Operating Procedures SUPERIZ Installation amp Operation Manual Zntage Engine AIR PARTS INC O 360 and 10 360 Series Engines CHAPTER 8 Servicing Requirements 1 GENERAL 2 LUBRICANTS This section specifies the fuel and lubricants A Oil grades are listed in Table 8 1 required to operate the Vantage series engines For aircraft servicing refer to the aircraft B Oil sump capacity is listed in manufacturer s manual Table 8 2 Table 8 1 Oil Grades All Models Average Ambient Air Recommended Grade Oil All Temperatures SAE 15W50 or 20W50 Co
28. spay atomized preservative oil MIL P 46002 Grade at room temperature through the upper spark plug hole of each cylinder with the piston at bottom dead center position Rotate crankshaft as opposite cylinders are sprayed Stop crankshaft with none of the pistons at top dead center 5 Drain preservative oil Re spray each cylinder To thoroughly cover all surfaces of the cylinder interior move the nozzle or spray gun from the top to the bottom of the cylinder 6 Install top spark plugs but do not install spark plug leads 7 Seal all engine openings exposed to the atmosphere using suitable plugs and covers 8 On aircraft tag each propeller in a conspicuous place with the following notation on the tag or if new or overhauled on the propeller flange Do Not Turn Propeller Engine Preserved Preservation Date Chapter 9 Engine Preservation amp Storage oo AN Note If the engine is not returned to flyable status on or before the 90 day expiration it must be preserved in accordance with Indefinite Storage procedures in this section 2 INDEFINITE STORAGE A Preparation for Storage 1 Remove oil sump drain plug and drain oil Replace drain plug torque and safety Remove oil filer Install new oil filter torque and safety Service engine to proper sump capacity with MIL C 6529 Type II oil 2 On aircraft Perform a ground run up Perform a pre flight inspection and correct any discrepan
29. the potential for vapor formation Vapor formation if extreme can cause engine stoppage due to lack of fuel Vapor formation in a minimal degree can cause lean operation of the engine that can lead to improper operation service ceiling restrictions or engine detonation under certain conditions March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i anlage Engine Note When running fuel lines for use with unleaded fuel do not use 90 fittings Instead use large radius bends to reduce the likelihood of vapor lock Also try to locate the fuel boost pump as close to the fuel tank as possible Periodically inspect non metallic fuel system components for degradation Aircraft boost pumps non engine driven may be used to supplement fuel flow to the engine driven fuel pump prevent vapor lock and aid in priming of fuel injected systems The maximum inlet pressure allowable at the engine driven fuel pump is defined in Table 3 of the Model Specification Data Although the use of aircraft boost pumps are not required for engine operation other than priming of fuel injection systems Superior Air Parts recommends their use as a backup to the engine driven fuel pump and as an aid in preventing vapor lock particularly when using motor gasoline The fuel system should be designed such that the minimum acceptable fuel pressure is available to the engine driven fuel pump at all
30. times without the use of an aircraft boost pump The minimum acceptable fuel pressure is defined in Table 3 of the Model Specification Data In addition the fuel system should be capable of providing at least 150 the maximum required flow of fuel to the engine driven fuel pump without the need for an aircraft boost pump See Table 1 of the Model Specification Data Fuel tanks should be vented to the atmosphere to prevent vacuum formation in the fuel tanks If un vented the pressure in the fuel tank as fuel is consumed can reduce to the point that the pressure available at the pump inlet is below the cavitation limit of the pump In this case cavitation can occur and engine stoppage due to fuel starvation is possible Superior Air Parts recommends the use of fuel flow meters as an aid to the pilot for proper engine management Two types of fuel flow meters are available for use in such systems those that indicate flow based upon sensed pressure and those that sense flow directly Chapter 3 Aircraft Engine Integration Considerations SUPERIZR R PARTIS Fuel flow meters that indicate flows based upon fuel system pressure can be less accurate than those that sense flow directly in times when abnormalities occur For example dirty fuel injectors or carburetor float malfunctions can cause increases or decreases to system pressure that would result in improper fuel flow indications for pressure based flow meters For this r
31. 6 Conical Mount Dimensions B Engine CG and Moment of Inertia The engine weight and location of the center of gravity are specified in Table 7 of the Model Specification Data Definitions for the variables used in Table 7 are illustrated in Figure 3a amp 3b of the Model Specification Data Moments of inertia are defined in Table 8 of the Model Specification Data The location of the center of gravity is defined with respect to the crankshaft centerline lateral and vertical dimensions and with respect to the crankcase backplane for the longitudinal dimension This data together with the appropriate data for additional components such as propeller assembly oil cooler and other engine and engine mount supported items provide sufficient information to locate the center of gravity with respect to the airframe March 2004 Superior Air Parts Inc C Engine Mount Design Loads Superior Vantage Engines are certified to meet the requirements of FAR 23 Acrobatic Category load factors for most engine and propeller combinations Table 3 3 lists the limit and ultimate load limits for the engine The term maneuvering moment of Table 3 3 relates to the force couple or moment produced by the weight of the engine propeller and accessories attached directly to the engine and the distance from the center of gravity of that assembly to the backplane of the crankcase These values represent the maximum moments limit and ultim
32. EL INJECTION MANIFOLD SPARK PLUG SPARK PLUG FUEL INJECTOR CHE ZO CHT PROBE LOCATION TYPICAL EACH HEAD ALTERNATOR amp BELT NOT PROVIDED WITH ENGINE STARTER FUEL INJECTION SERVO Figure 1 6 10 360 Engine Front View March 2004 Superior Air Parts Inc Chapter 1 Engine Description SUPERIZR Installation amp Operation Manual Vantage Engine OUO O 360 and 1O 360 Series Engines CYLINDER ASSEMBLY FUEL INJECTION MANIFOLD CRANKCASE ASSEMBLY ACCESSORY HOUSING STARTER SUPPORT ASSEMBLY OIL FILTER TN WIRING HARNESS MAGNETO FUEL PUMP STARTER ko FUEL LINE FUEL INJECTION SERVO SPARK PLUG OIL SUMP Figure 1 7 IO 360 Engine Left Side View March 2004 Superior Air Parts Inc Chapter 1 Engine Description SUPERIZ Installation amp Operation Manual Zntage Engine WE O 360 and 10 360 Series Engines FUEL INJECTION MANIFOLD FUEL INJECTIOR AU EM ss ix l TD IK J OAA JL TIT I TT Mal nf Il 24 9 p a UI li I lips III ss a luma Aa gt 8 Im 3 elim eer Nr se usu Tie CH DNH Figure 1 8 10 360 Engine Top View March 2004 Superior Air Parts Inc Chapter 1 Engine Description SUPERIZR Installation amp Operation Manual Sanne Engine RM m O 360 and 10 360 Series Engines ALTERNATE OIL TACHOMETER CONNECTION TO COOLER OIL TEMP CONNECTION VACCUM PUMP ACCESSORY PAD
33. HAND AS DURING PREFLIGHT THE ENGINE MAY START AND CAUSE INJURY TO PERSONNEL THIS TYPE OF MALFUNCTION SHOULD BE CORRECTED PRIOR TO CONTINUED OPERATION OF THE ENGINE CAUTION DO NOT UNDERESTIMATE THE IMPORTANCE OF PRE TAKEOFF MAGNETO CHECK WHEN OPERATING ON SINGLE IGNITION SOME RPM DROP SHOULD BE NOTED NORMAL INDICATIONS ARE 25 75 RPM DROP AND SLIGHT ENGINE ROUGHNESS AS EACH MAGNETO IS SWITCHED OFF AN RPM DROP IN EXCESS OF 150 RPM MAY INDICATE A FAULTY MAGNETO OR FOULED SPARK PLUGS 4A Controllable pitch propeller Check for ignition problems with propeller in Low Pitch High RPM and set the throttle to approximately 1700 RPM A Move propeller governor control toward low RPM position and observe tachometer Engine speed should decrease to minimum governing speed 200 300 RPM drop Return governor control to high speed position Repeat this procedure two or three times to circulate warm oil into the propeller hub B Where applicable move propeller control to feather position Observe for 300 RPM drop below minimum governing RPM then return control to full increase RPM position 4B Fixed pitch propeller Aircraft that are equipped with fixed pitch propellers may check magneto drop off with engine operating at approximately 1700 RPM 5 Check magnetos Move the ignition switch first to R position and note engine RPM then move switch back to BOTH position to clear the other set of spark plugs Move the switch to L
34. Mixture Curves E Minimum Oil Quantity F Fuel Pressure and Flow Requirements G Fuel Grade Requirements H Oil Pressure and Temperature Limits I Operating Conditions J Accessory Temperature Limits March 2004 Superior Air Parts Inc 3 OPERATION INSTRUCTIONS Note The Vantage series engines have been carefully run in by Superior Air Parts but requires further break in until oil consumption has stabilized After this period a change to approved ashless dispersant oil should be made Refer to the Special Procedures Chapter Five Break in Instructions Superior Vantage Engines are certified for 100LL Avgas per ASTM D910 91 98 lead optional Avgas per ASTM D910 and Motor Gasoline with a minimum antiknock index R M 2 method of 91 per ASTM D4814 The Vantage series engine can operate and perform at a rated power using auto fuel of at least 91 Octane R M 2 without alcohol The higher the octane the greater the detonation margin during high power and or hot operation When operating on unleaded fuel Superior Air Parts recommends using fresh premium 91 minimum Octane auto fuel available at major brand stations Due to the higher vapor pressure of auto fuel carburetor icing and vapor lock are more likely The use of motor gasoline is prohibited with fuel temperatures over 85 F altitudes at 12 500 feet MSL and over 110 F at Sea Level The following states require compliance with D 4814 or require critical sp
35. Model Carburetor Starter Plug Magneto Magneto Pump Harness 0 360 Unison Unison Precision Aero Acc SkyTec Unison 4371 4371 MA 4 5 AF 15472 149 12LS M4001 Table 7 Engine Weight amp Location of Center of Gravity Center of Gravity Weight X Y Z Engine Lb In In In O 360 Axxx 288 lbs 44 2 74 7 10 O 360 Bxxx 291lbs 50 2 80 7 05 For definition of X Y and Z see figures 3a amp 3b Table 8 Engine Moment of Inertia Moment of Inertia About the Center of Gravity Roll Pitch Yaw Engine Model In Lbi Sec In Lbr Sec In Lb Sec O 360 Axxx 49 0 40 2 65 9 O 360 Bxxx 49 2 49 5 67 1 17 Appendix A O 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data k EE Engine ds O 360 Series Engine Table 9 Oil Temperature Limits Minimum for Take off 75 F Maximum Allowable 240 F Recommended Cruising 130 F 200 F Table 10 Fuel Grade Requirements Model Aviation Grade Fuel Minimum Octane Motor Fuel O 360 91 98 Lead Optional 91 Table 11 Operating Conditions Max Oil e Fuel Cons Max Cyl Operation RPM MAP HP Cons Lbs Hr Qts Hr Head Temp 108 e Maximum Rated 2700 WOT 180 Best Pwr 75 500 F Performance 72 Cruise 8096 2500 26 144 Best Pwr 50 500 F Rated Economy Cruise e 52 2 60 Rated 2400 24 108 Peak EGT A0 500 F Table 12 Accessory Temperature Limits Magnetos 185 F Ambient Starter None Fuel Pump
36. NNNNNNNNNDDONDDADNAADNDANAADAWWWHH N2Z i anlage Engine Page D N np ER gt C G G D D O O iO Q N O QQ p OO N D N S gt p c SUPERIAR Installation amp Operation Manual O 360 and 10 360 Series Engines N2Z i anlage Engine Introduction About This Manual This engine installation and operation manual is provided as guidance for the installation and installation design of a Superior Vantage Engine to an airframe and to describe its operational characteristics Its purpose is to provide technical information to aid in designing and operating an effective engine installation so as to achieve maximum performance while providing for maximum service life Superior Air Parts has made clear and accurate information available for those who maintain own and repair the Vantage O 360 and 10 360 Series Engines Superior Air Parts values your input regarding revisions and additional information for our manuals Please forward your comments and input to Superior Air Parts Attn Engineering Department 621 South Royal Lane Suite 100 Coppell Texas 75019 Related Publications The following are related engine and accessory publications O amp IO 360 Maintenance Manual SVMMO1 O amp 10 360 Overhaul Manual SVOMO1 O amp O 360 lllustrated Parts Cat SVIPCO1 Unison Master Service Manual F 1100 Precision RSA 5 Service Manual 15 338 Precision MA 4 5 Manual MSAHBK 1 Champion Aerospace Service Manual AV 6R
37. Operation Manual They must also be maintained in accordance with the applicable Overhaul Manual and other Instructions for Continued Airworthiness Superior accepts no responsibility for airworthiness of any aircraft resulting from the installation of the engine or associated equipment SUPERIZ Installation amp Operation Manual Zntage Engine ED i O 360 and 10 360 Series Engines Obtaining Service Information All Vantage Series Engine manuals and service information may be downloaded at www superior air parts com All Vantage Series Engine manuals and service information may also be purchased by contacting Superior Air Parts 621 South Royal Lane Suite 100 Coppell Texas 75019 or call 972 829 4600 March 2004 Superior Air Parts Inc Accessory Information may be obtained at www championaerospace com www unisonindustries com www skytecair com www precisionairmotive com www aeroaccessories com SUPERIZ R PARTS NC Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i anlage Engine CHAPTER 1 Engine Description 1 GENERAL DESCRIPTION Superior Vantage Engines are four cylinder horizontally opposed air cooled direct drive powerplants incorporating a wet sump bottom mounted induction bottom exhaust with either carbureted or port injected fuel systems Provisions exist for both front and rear mounted accessories All engine components will be referenced as they are
38. RNING AN ENGINE TO SERVICE AFTER STORAGE A Remove all seals and all desiccant bags B Remove cylinder dehydrators and plugs or spark plugs from upper and lower spark plug holes C Remove oil sump drain plug and drain the corrosion preventive mixture Replace drain plug torque and safety Remove oil filter Install new oil filter torque and safety Service the engine with oil in accordance with the manufacturer s instructions WARNING TO PREVENT THE POSSIBILITY OF SERIOUS BODILY INJURY OR DEATH BEFORE MOVING THE PROPELLER DO THE FOLLOWING A VERIFY ALL SPARK PLUG LEADS ARE DISCONNECTED B VERIFY MAGNETO SWITCHES ARE CONNECTED TO MAGNETOS AND THAT THEY ARE IN THE OFF POSITION AND P LEADS ARE GROUNDED C THROTTLE POSITIONS CLOSED D MIXTURE CONTROL IDLE CUT OFF E SET BRAKES AND BLOCK AIRCRAFT WHEELS ENSURE THAT AIRCRAFT TIE DOWNS ARE INSTALLED AND VERIFY THAT THE CABIN DOOR LATCH IS OPEN F DO NOT STAND WITHIN THE ARC OF THE PROPELLER BLADES WHILE TURNING THE PROPELLER March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i anlage Engine D Rotate propeller by hand several revolutions to remove preservative oil E Service and install spark plugs and ignition leads in accordance with the manufacturer s instructions F Service engine and aircraft in accordance with the manufacturer s instructions G Thoroug
39. STEM The fuel system design can significantly effect both performance and longevity of an aircraft engine installation In addition to the obvious performance aspects fuel systems that limit the fuel supply can promote engine detonation and vapor lock Un damped and extreme pressure pulsations can cause malfunction of the fuel metering systems A Fuel System Requirements and Filtration Superior Vantage Engines are supplied with positive displacement fuel pumps that are directly driven by the engine These pumps are designed to provide the appropriate flow and pressure to the fuel metering devices according to their requirements The aircraft fuel system should be capable of providing at least twice the maximum engine fuel flow requirements to minimize the potential for vapor formation The fuel flow requirements are defined in Table 1 of the Model Specification Data The flow of fuel must be vapor free water free and filtered to be free of foreign objects or debris The foreign object filter requirements are defined in Table 2 of the Model Specification Data B General Fuel System Design The aircraft fuel system should be designed so flow restrictions do not occur in the piping system Flow restrictions in this context refer to system conditions such as sharp radius bends abrupt changes in pipe diameter larger or smaller tee and other fittings valves etc In addition to limiting maximum fuel flow flow restrictions increase
40. See Chapter 6 Operating Instructions for Fuel Temp Limits 18 Appendix A O 360 Model March 2004 Superior Air Parts Inc Specification Data N27 antage Engine 10 360 SERIES ENGINE MODEL SPECIFICATION DATA APPENDIX B SUPERIZR A IR PAR T LINE SUPERIZR AIR PART Figures mo 01 En 10 11 12 13 14 Tables Joo ND N March 2004 Superior Air Parts Inc Model Specification Data 10 360 Series Engine APPENDIX B TABLE OF CONTENTS Induction Airflow Requirements Inter Cylinder Baffle Performance Location of Engine Center of Gravity Horizontal Location of Engine Center of Gravity Vertical 10 360 Installation Drawing Front View 10 360 Installation Drawing Top View Fuel Injection Installation Drawing Propeller Load And Full Throttle Curves Altitude Performance At Best Power Cruise Performance Map 80 Power Cruise Performance Map 70 Power Cruise Performance Map 60 Power Fuel Mixture Curve 75 Power Fuel Mixture Curve 65 Power Minimum Oil Quantity Maximum Fuel Flow Requirements Fuel Filter Requirements Fuel Pump Inlet Pressure Limits Oil Heat Rejection Airside Heat Rejection Crankcase Pressure Oil Pressure Limits Engine Accessories Engine Weight amp Location of Center of Gravity Engine Moment of Inertia Oil Temperature Limits Fuel Grade Requirements Operating Conditions Accessory Temperature Limits N27 anlage E
41. Series Engines Table 1 2 Manufacturer s Physical Specifications Heigh Width Length Model m t E E Weight O 360 24 6 33 4 32 8 See MSD 10 360 24 0 33 4 32 8 See MSD Table 1 3 Views of the Engine Engine View Figure Number Location O 360 Engine Front View Figure 1 2 p 5 O 360 Engine Left Side View Figure 1 3 p 6 O 360 Engine Top View Figure 1 4 p 7 O 360 Engine Rear View Figure 1 5 p 8 10 360 Engine Front View Figure 1 6 p 9 10 360 Engine Left Side View Figure 1 7 p 10 10 360 Engine Top View Figure 1 8 p 11 10 360 Engine Rear View Figure 1 9 p 12 March 2004 Superior Air Parts Inc Chapter 1 Engine Description SUPERIZ Installation amp Operation Manual Zntage Engine WE O 360 and 10 360 Series Engines SPARK PLUG SPARK PLUG CHT PROBE LOCATION TYPICAL EACH HEAD PRIMING SYSTEM ALTERNATOR amp BELT NOT PROVIDED WITH ENGINE e L Ha Pd b STARTER THROTTLE LEVER P4 FUEL LINE CARBURETOR Figure 1 2 e O 360 Engine Front View March 2004 Superior Air Parts Inc Chapter 1 Engine Description SUPERIZR Installation amp Operation Manual Vantage Engine WE O 360 and 10 360 Series Engines CYLINDER ASSEMBLY ACCESSORY CRANKCASE HOUSING ASSEMBLY STARTER SUPPORT ASSEMBLY FILTER HARNESS we hr db PRIMING SYSTEM SPARK PLUG STARTER INDUCTION OIL SUMP SYSTEM ASSEMBLY CARBURETOR Figure 1 3 O 360 Engine Left Side View March
42. VP m Airworthiness Limitations Aircraft Engine Integration Considerations General Induction System Fuel System Engine Cooling Exhaust Lubrication System Propeller Attachment Electrical System Engine Controls 0 Engine Accessories 1 Engine Mounting O EE ONS Engine Installation 1 General Instructions 2 Preparing Engine For Service 3 Installation of Engine 4 Instrumentation Connections Special Procedures General Break In Procedures Special Tools And Equipment Break In Procedures General Inspection Check Daily Pre Flight Inspection Quop Co DO Normal Operating Procedures 1 General 2 Engine Operation And Limits 3 Operation Instructions March 2004 Superior Air Parts Inc N27 i anlage Engine Page Number i ii iii N N sch moooom gt D N wow sch SUPERIZ Installation amp Operation Manual ee ee O 360 and 10 360 Series Engines Table Of Contents continued Chapter 7 Abnormal Operating Procedures General Engine Will Not Start Rough Idling Engine Not Able to Develop Full Power Rough Engine Operation Low Power and Engine Runs Rough Low Oil Pressure On Engine Gage High Oil Temperature Excessive Oil Consumption NO O1 e D Chapter 8 Servicing Requirements 1 General 2 Lubricants 3 Fuels 4 Consumables Chapter 9 Engine Preservation And Storage 1 Temporary Storage Indefinite Storage 2 3 Inspectio
43. Zi 7 8 Chapter 7 Abnormal Operating Procedures SUPERIZR Installation amp Operation Manual Zntage Engine R PARTS 2 ENGINE WILL NOT START O 360 and 10 360 Series Engines Table 7 2 Engine Will Not Start Probable Cause No Fuel Excessive Priming Defective ignition wire Dead battery Malfunction of magneto breaker Lack of sufficient fuel flow Water in fuel injector or carburetor Internal failure 3 ROUGH IDLING Correction Fill with fuel Leave ignition Off and mixture control in Idle Cut Off open throttle and clear cylinders by cranking a few seconds Turn ignition switch On and proceed to start Check with electric tester and replace any defective wires Replace battery Clean points Check internal timing of magnetos Disconnect fuel line and check fuel flow Drain fuel injector or carburetor and fuel lines Check oil screens for metal particles If found complete overhaul of the engine may be required Table 7 3 Rough Idling Probable Cause Incorrect idle mixture Leak in the induction system Incorrect idle adjustment Uneven cylinder compression Faulty ignition system March 2004 Superior Air Parts Inc Correction Adjust mixture Tighten all connections in the induction system Replace any damaged parts Adjust throttle stop to obtain correct idle Check condition of piston rings and valve seats Check entire ignition system Chapter 7 Abnormal Operating Procedures
44. ak Operation 30 29 N N N N N A o o N o Absolute Dry Manifold Pressure In Hg N o 21 50 84 Fuel Flow Lb Hr Figure 10 Cruise Performance Map 70 Power 11 Appendix B 10 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data a RE 10 360 Series Engine Cruise Performance Superior Vantage O IO 360 Series 60 Power 108 Hp Rich of Peak Operation 28 27 N o N o N A 23 Absolute Dry Manifold Pressure In Hg N N N 20 Elei gen le gl ERE E Fuel Flow Lb Hr Figure 11 Cruise Performance Map 60 Power 12 Appendix B 10 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data Vintage Engine oe Nes 10 360 Series Engine Performance Cruise Fuel Mixture Curve Superior Vantage IO 360 Series 26 in Hg x 2400 RPM 0 Pid EE FFF ies cease cece ED pag Eee Ee a 1 50 L U l Edi se HB T TPS EE E E Ee ee e ICT jt bb oe oo oe oars Se ee Ee ES eos EE GE e Fe SE BEE 46 48 50 52 54 56 58 60 62 64 66 68 70 72 74 76 78 80 82 Fuel Flow Lb Hr Figure 12 Fuel Mixture Curve 75 Power 13 Appendix B 10 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data Vintage Engine oe Nes 10 360 Series Engine Economy Cruise Fuel Mixture Curve Superior Vantage 10 360 Series 24 in Hg x 2400 RPM
45. ame manufacturer due to the wide range of electrical system requirements among aircraft A mounting pad is provided on the crankcase near the nose of the engine for this purpose A V belt pulley is also provided as part of the flywheel Tension of the belt should be adjusted per manufacturers recommendations See page 22 for V belt and alternator installation information Chapter 3 Aircraft Engine Integration Considerations SUPERIZR Installation amp Operation Manual k Engine GYM FR O 360 and 10 360 Series Engines Firing Order Clockwise Rotation 1 3 2 4 Ignition Wiring Diagram olala Figure 3 2 Ignition Wiring Diagra
46. anual UN Engine RES UNS O 360 and 10 360 Series Engines Chapter 3 Aircraft Engine Integration Considerations SUPERIZR R PARTIS 4 ENGINE COOLING The engine cooling system design can significantly effect both performance and longevity of an aircraft engine installation High engine temperatures can result in loss of power fuel vapor lock and can promote accelerated wear and even engine detonation A General Cooling System Design The Superior Vantage Engine is a horizontally opposed air cooled design As such all heat is removed from the engine either by airflow over the cylinders and crankcase or through an air to oil lubricant heat exchanger The horizontally opposed cylinder arrangement is a space efficient design that allows maximum cooling airflow with minimum drag In general air cooling of the engine heads and crankcase occurs by directed airflow over those components Air is commonly received into the cowl in a plenum above the engine and directed downward between the cylinder and barrel fins to a volume within the lower cowl The cooling air normally exits the lower cowl through the exhaust tailpipe exit area Airflow over the engine is governed by the pressure differential between the upper cowl and lower cowl areas In high performance installations cowl flaps may be added to increase the cooling airflow Superior Vantage Engines are provided with inter cylinder metal baffles to aid in the control of
47. any aerobatic installations However provisions exist to attach an aerobatic oil system to the Superior Vantage Engine if desired For more information regarding aerobatic installations contact Superior Air Parts The maximum capacity of the oil sump is 8 U S quarts Oil quantities in excess of this amount can cause loss of engine efficiency due to splashing and fluid drag of internal components through the oil and also pumping of the oil out the crankcase breather fitting Minimum oil capacity is governed by the ability of the oil pump to draw full oil i e no entrained air from the sump in various flight attitudes 2 Oil Pump and Pressure Control Valve Superior Vantage Engines employ a high flow positive displacement gear pump to provide oil throughout the engine The pump is capable of producing oil flow and pressure values much higher than those required by the engine as a safety measure to ensure that the necessary oil is always available to the engine Because of this a pressure control valve is used to govern the maximum oil pressure in the system Oil pressures that are too high will promote external leaks that would not otherwise occur The oil pressure control valve is adjustable so that the operator may ensure that the oil pressure is within specified limits If oil pressure under normal operating conditions always exceeds the maximum or minimum specified limits as defined in Table 5 of the Model Chapter
48. are certified for 100LL Avgas per ASTM D910 91 98 lead optional Avgas per ASTM D910 and Motor Gasoline with a minimum antiknock index R M 2 method of 91 per ASTM D4814 Higher octane fuel improves the detonation margin during high power and or hot operation When operating on unleaded fuel Superior recommends using fresh premium auto fuel available at a major brand reputable gas station The use of auto fuel blended with alcohol ethanol is forbidden Winter oxygenated ethanol fuel blends or reformulated gasoline are typically most available during the colder months for smog reduction Ethanol alcohol mixed with unleaded fuel can cause vapor lock carburetor ice reduction in range carburetor problems and damage to the fuel system The use of an alcohol and water tester is recommended Acceptable gasoline is specified per ASTM D 4814 European EN228 again without alcohol When running fuel lines for an airplane intended for unleaded auto fuel operation it is very important to address issues that can reduce the likelihood of vapor lock For example replace 90 fittings with smooth tubing bent to a larger radius and do not use expansion or contraction fittings Locate the fuel boost pump as close to the fuel tank as possible Non metallic fuel system components should be manufactured from materials that are known to be compatible with auto fuels March 2004 Superior Air Parts Inc Installation amp Operation M
49. ate that may be imposed on the engine mount structure 24 Chapter 3 Aircraft Engine Integration Considerations SUPERIZR R PARTIS The installation of an engine per 14CFR Part 23 FAR 23 includes the use of several Factors of Safety When performing the engine installation design for a Superior Vantage Engine the weight and location for the center of gravity of the engine propeller and all engine mounted accessories must be considered together with the appropriate Factors of Safety from FAR 23 for the flight category desired The resulting positive and negative maneuvering loads for the installation must be within the limits shown in Table 3 3 For convenience Figure 3 7 illustrates the above load limits Table 3 3 in terms of vertical forces as a function of the Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i anlage Engine longitudinal center of gravity The term engine torque in Table 3 3 relates to the average output torque of the engine at maximum rated speed plus design factors as required by 14CFR Part 33 When performing the engine installation design for a Superior Vantage Engine it is required that the average output torque at maximum rated speed and power be below these values The limit load engine torque of 1634 Ft Lb corresponds to a power output of approximately 210 Hp at 2700 RPM including design factors Table 3 3 Limit and Ultimate Engine Mount Loads Limit Load
50. ation amp Operation Manual O 360 and 10 360 Series Engines WZ i antage Engine 4 CONSUMABLES The Vantage Series Engines are equipped with spark plugs and a spin on oil filter Table 8 4 specifies these consumable items and their corresponding part number Table 8 4 Consumables Spark Plugs Champion Aviation P N REM40E Unison Industries P N UREM40E Oil Filter Champion Aviation P N CH48108 amp CH48108 1 Chapter 8 Servicing Requirements A IS Installation amp Operation Manual O 360 and IO 360 Series Engines WZ i antage Engine CHAPTER 9 Engine Preservation And Storage There is no practical procedure that will ensure corrosion prevention on installed aircraft engines The degree of corrosion is influenced by geographical locations season and usage The owner operator is responsible for recognizing the conditions that are conducive to corrosion and for taking appropriate precautions Corrosion can occur in engines that are flown only occasionally regardless of geographical location In coastal areas and areas of high humidity corrosion can occur in as little as a few days The best method for reducing the likely hood of corrosion is to fly the aircraft at least once every week for a minimum of one hour Note Corrosion may reduce engine service life Of primary concern are cylinders piston rings camshaft and lifters 1 TEMPORARY STORAGE A Preparation for Storage 1 Remove oil sump dra
51. ature 1 receive MS28034 1 Oil Temperature Sensor or Fig 1 5 Fig 1 9 equivalent Oil Pressure 1 1 8 27 NPT Fig 1 5 Fig 1 9 Manifold i i Rees 1 1 8 27 NPT Fig 1 5 Fig 1 9 Tachometer 4 Standard Tach Drive Connection 5 32 Square Drive pi 1 5 Fio 1 9 Drive Socket with 7 8 18 UNS Cap Threads 9 9 E App A App B Fuel Pressure 1 1 8 27 NPT Table3 Table 3 March 2004 Superior Air Parts Inc Chapter 4 Engine Installation A SUPERIZR R P Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i anlage Engine CHAPTER 5 Special Procedures 1 GENERAL BREAK IN PROCEDURES This section provides the Break In Procedures to achieve satisfactory ring seating and long cylinder life On all new Vantage engines after top overhaul or major engine overhaul break in is critical Always refer to the latest Superior Service Data on Break In instructions Note Refer to the engine warranty Violation of these procedures will void the engine s warranty 2 SPECIAL TOOLS AND EQUIPMENT Standard aviation shop tools are required The aircraft can be a suitable test stand for running in cylinders March 2004 Superior Air Parts Inc 3 BREAK IN PROCEDURES WARNING OPERATION OF A DEFECTIVE ENGINE WITHOUT A PRELIMINARY EXAMINATION CAN CAUSE FURTHER DAMAGE TO A DISABLED COMPONENT AND POSSIBLE INJURY TO PERSONNEL MAKE SURE THOROUGH INSPECTION AND TROUBLESHOOTING PROCEDURES ARE ACCOMPLISHED THIS WILL HELP TO
52. awn into the pressurized portion of the oil system In addition Superior Vantage Engines are provided with a full flow oil filter to maintain contaminant free oil and promote long engine life Superior recommends changing the full flow oil filter inspecting cleaning the suction screen filter and changing the oil in accordance with published maintenance schedules In addition to clean oil of the proper viscosity it is important to ensure that the oil is free of aeration and foam in the pressurized portion of the oil system This can become an issue at high altitudes as the vapor pressure of the oil exceeds the ambient pressure Severe aeration within the anticipated flight altitudes of a Superior Vantage normally aspirated engine but must be verified through flight testing March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and IO 360 Series Engines 12 WZ i anlage Engine B Lubricating System Components The lubricating system of Superior Vantage Engines is composed in general of an oil sump or reservoir an oil cooler circuit an internal pressurized circuit and for installations with constant speed propellers a propeller governor circuit A schematic of the lubricating system is provided in Figure 3 1 1 Oil Sump Superior Vantage Engines utilize a wet sump design That is the engine oil sump is the primary reservoir for engine oil as opposed to a remote reservoir as is done in m
53. cantly effect the performance of the oil cooler and sizing should be chosen accordingly Although the reduced temperature of the air can increase the efficiency of the cooler due to a larger temperature difference between the hot oil and the cooling air the reduced air density is generally a larger consideration and will result in an overall reduction in cooler efficiency at higher altitudes Therefore cooler sizing calculations should be made with the air density appropriate for the maximum intended altitudes of the installation March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i anlage Engine D Accessory Cooling Typically engine cowl baffles effectively separate the upper cowl plenum from the lower cowl plenum through the axes of the cylinders However the rear cowl baffle is typically attached to the engine crankcase and therefore most engine accessories are behind the rear cowl baffle or below the cylinder axes and therefore part of the lower cowl plenum Unless otherwise provided these accessories are located in an area of relatively stagnant air that has already passed over the engine for airside cooling or has passed through the oil cooler Because of the elevated temperature of the air surrounding these accessories and the relative lack of airflow around them it is often necessary to add small supplementary ducts to provide cooling air The amo
54. cies Fly the aircraft for at least one hour or run on ground until 180 F operating temperature is reached Don t exceed 400 F cylinder head temperature 3 On test cell Perform run up to warm engine to operating temperature Run at operating temperature for a minimum of 15 minutes WARNING TO PREVENT POSSIBILITY OF SERIOUS BODILY INJURY OR DEATH BEFORE MOVING THE PROPELLER DO THE FOLLOWING A DISCONNECT ALL SPARK PLUG LEADS B VERIFY MAGNETO SWITCHES ARE CONNECTED TO MAGNETOS AND THAT THEY ARE IN THE OFF POSITION AND P LEADS ARE GROUNDED C THROTTLE POSITION CLOSED D MIXTURE CONTROL IDLE CUT OFF E SET BRAKES AND BLOCK AIRCRAFT WHEELS ENSURE THAT AIRCRAFT TIE DOWNS ARE INSTALLED AND VERIFY THAT THE CABIN DOOR LATCH IS OPEN F DO NOT STAND WITHIN THE ARC OF THE PROPELLER BLADES WHILE TURNING THE PROPELLER March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and 10 360 Series Engines N27 i anlage Engine 4 After flight remove all spark plug leads and remove the top spark plugs Protect the ignition lead ends with AN 4060 Protectors Install protective plugs in bottom spark plug holes Using a common garden sprayer or equivalent spay atomized preservative oil MIL P 46002 Grade at room temperature through the upper spark plug hole of each cylinder with the piston at bottom dead center position Rotate crankshaft as opposite cylinde
55. consider these loads and ensure that natural frequencies of the airframe do not match these forcing functions during prolonged operation Although these loads will vary depending upon choices of mount style propeller and accessories Superior has measured the transmitted vibratory loads for a typical installation Figures 3 8 and 3 9 illustrate forcing functions produced by the March 2004 Superior Air Parts Inc 26 engine on the engine on a typical engine mount design Data is presented for startup and shutdown sequences in Figure 3 8 and steady state power settings in Figure 3 9 Proper installation design requires that testing be performed to verify that vibratory loads are acceptable for the specific airframe isolator style engine propeller and accessories Further the stresses introduced to the engine mount must be verified to assure proper function and resistance to fatigue This is separate from the issue of propeller limitations based on strain gauge testing of the engine crankshaft Chapter 3 Aircraft Engine Integration Considerations SUPERIZ Installation amp Operation Manual Zntage Engine AIR PARTS INC O 360 and 10 360 Series Engines Engine Forcing Functions on Firewall Start Up amp Shut Down Operation Superior Vantage O IO 360 oll fomonl jet Go lasa lin Ni clio LS Banding Horizontal r Se RE ee tau ee SE hee a Sak air win Ese Qa kd e L Bending Vertical T T T
56. d pressure losses in the oil system not only cause inefficiencies in the overall engine system but also add to the potential for aeration during high altitude flight March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and IO 360 Series Engines 13 WZ i anlage Engine C Crankcase Ventilation Pressure is generated within the crankcase during normal engine operation primarily as a result of piston ring blow by If the crankcase pressure were not controlled nose seal and other seal failures would occur leading to loss of oil Superior Vantage Engines utilize crankcase breather circuits as a means of controlling crankcase pressure See Table 4 of the Model Specification Data for specific measurements defining crankcase pressures The installation design should include provisions to connect a crankcase ventilation hose to the engine breather fitting on the rear of the engine The purpose of this hose is to direct the crankcase gas safely overboard It is recommended that an air oil separator be used to prevent oil entrained in the gas flow from getting on the airframe If an air oil separator is used the oil drain may be connected into a cylinder head drain back tube or other location as approved by Superior Air Parts Care should be taken in the location of the breather tube exit so as not to create a positive or negative pressure in the breather circuit A positive pressure would serve to aggrava
57. draulic fluid as well as dry combustible materials B Exhaust System Design and Sizing Several styles of exhaust systems are commonly used in piston aircraft engines Engines with smaller power ratings sometimes use stub or direct exhaust systems These systems simply provide a short section of exhaust pipe to direct the exhaust gas away from the cylinder head and are not connected with each other While these systems are typically the loudest and least beneficial in terms of performance enhancement they can hold the benefit of being the lightest design Although it is possible to use this type of system on Superior Vantage Engines it is not the recommended approach Another exhaust design style is to connect 2 or 4 of the exhaust tubes together before exiting the March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i anlage Engine aircraft Commonly referred to as 2 into 1 or 4 into 1 systems these designs feature a space efficient way to transport the exhaust gas safely overboard Although these systems are not designed to add substantial performance benefits to the engine they can rob power and efficiency if not properly designed The intersections of the exhaust pipe segments must be designed such that pressure pulsations traveling down a given exhaust pipe do not adversely effect the operation of cylinders with intersecting pipes If pressure pulsa
58. e In Hg N N N N N o A on N ch 20 pun HH A ELFEN ERE EA AU H o o o ES v o Tiz o LE pa Fuel Flow Lb Hr Figure 11 Cruise Performance Map 60 Power March 2004 Superior Air Parts Inc 12 Appendix A O 360 Model Specification Data SUPERIZR Model Specification Data Vintage Engine oe Nes O 360 Series Engine Performance Cruise Fuel Mixture Curve Superior Vantage O 360 Series 26 in Hg x 2400 RPM erp ee L a E E Below Peak EGT E SET SEET j EE T a PSS Md TT HET 75 140 WEE Se SE EE ESE SE E EE ES 110 100 90 80 0 70 0 65 0 60 0 55 0 50 BE ES ES EUR nes eee eee eee Sen j j j j Ee 49 51 53 55 57 59 61 63 65 67 69 71 73 75 77 79 81 83 Fuel Flow Lbs hr Figure 12 Fuel Mixture Curve 75 Power 13 Appendix A O 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data Vintage Engine oe Nes O 360 Series Engine Economy Cruise Fuel Mixture Curves Superior Vantage O 360 Series 24 in Hg x 2400 RPM Eun oe oe eee eee ones sees ES Gee ein ot HEI Eeer on aS E TT Below Peak Below Peak CHT F PABEBEBHB 46 48 50 52 54 56 58 60 62 64 66 68 70 72 74 76 Fuel Flow Lbs hr Figure 13 Fuel Mixture Curve 65 Power 14 Appendix A O 360 Model March 2004 Superior Air Parts Inc Specification Data AIR PART SUPERIZR Model Specification Da
59. e Review all probable causes given Testing is limited to the continuity checks of the ignition wiring harness The fault isolation sequence is in order of approximate ease of checking not necessarily in order of probability WARNING OPERATION OF A DEFECTIVE ENGINE WITHOUT A PRELIMINARY EXAMINATION CAN CAUSE FURTHER DAMAGE TO A DISABLED COMPONENT AND POSSIBLE INJURY TO PERSONNEL MAKE SURE THOROUGH INSPECTION AND TROUBLESHOOTING PROCEDURES ARE ACCOMPLISHED THIS WILL HELP TO PREVENT INJURIES TO PERSONNEL AND OR DAMAGE TO THE EQUIPMENT Symptom Engine will not start Rough Idling Engine Not Able to Develop Full Power Rough Engine Operation Low Power and Engine Runs Rough Low Oil Pressure On Engine Gage High Oil Temperature Excessive Oil Consumption March 2004 Superior Air Parts Inc WARNING FUEL IS TOXIC AND FLAMMABLE DO NOT BREATHE VAPORS USE IN A WELL VENTILATED AREA FREE FROM SPARKS FLAME OR HOT SURFACES PUT ON SPLASH GOGGLES SOLVENT RESISTANT GLOVES AND OTHER PROTECTIVE GEAR IN CASE OF EYE CONTACT FLUSH WITH WATER FOR 15 MINUTES AND SEEK MEDICAL ATTENTION IN CASE OF SKIN CONTACT WASH WITH SOAP AND WATER WARNING HOT OIL MAY CAUSE BURNS TO EYES AND SKIN PUT ON SPLASH GOGGLES INSULATED GLOVES AND OTHER PROTECTIVE GEAR IN CASE OF EYE CONTACT FLUSH WITH WATER FOR 15 MINUTES AND SEEK MEDICAL ATTENTION IN CASE OF SKIN CONTACT WASH WITH SOAP AND WATER Table 7 1 7 2 7 3 7 4 7 5 7 6
60. e system designs outlined in this chapter be proven prior to activation of the warranty Proper functioning of the installation design shall be proven by technical data such as test data photographs drawings and engineering calculations Superior Air Parts Engineering Department will provide guidance regarding the specifics of these requirements as appropriate to the installation and on a case by case basis Throughout this chapter reference is made to data contained in the Model Specification Data These documents are engine series specific and are contained in Appendices of this manual Refer to the appropriate Model Specification Data for your engine model when consulting this data 2 INDUCTION SYSTEM The induction system design can significantly effect both performance and longevity of an aircraft engine installation In addition to more obvious issues such as air filtration seemingly insignificant design features can cause restrictions or other airflow disturbances resulting in flow loss or improper function of the fuel metering system Induction systems which yield excessive intake air temperatures can promote engine detonation A General Induction System Design It is important that the induction system of naturally aspirated engines such as the Superior March 2004 Superior Air Parts Inc Vantage Series be capable of supplying clean filtered cool intake air to the engine at the maximum required flowrate and wit
61. e and oil before depend on the forward speed of the aircraft to starting Preheating normally takes 20 to 30 cool properly It is recommended that the minutes to assure that all lines and all parts of following precautions be observed to prevent the engine are uniformly warmed Warm air overheating should be forced up through the bottom of the cowl to reach the oil filter sump area and intake Ground Running Any ground check that manifold Additional heated air should be requires full throttle operation must be limited to directed over the top of the engine to reach the three minutes or less the cylinder head cylinders and cooler Once an engine is temperatures should not exceed the maximum preheated it can be started but should be run CHT of 500 F for 5 to 10 minutes at idle settings not to exceed 1 000 RPM Verify oil pressure which can take up to 45 seconds to rise to the minimum of 20 psi lf a full minute goes by without reaching a proper oil pressure setting the engine should be shut down and inspected March 2004 Superior Air Parts Inc Chapter 6 Normal Operating Procedures SUPERIZR Installation amp Operation Manual Vintage Engine we O 360 and 10 360 Series Engines Table 6 3 Ground Running Fixed Wing Warm Up 1 Head the Aircraft into the wind 2 Leave mixture control Full Rich for the entire warm up period This setting is dependent upon flight elevation pressure altitude 3 Operate only with the
62. e exhaust port protective plugs Service the lubrication system in accordance with instructions from Chapter 5 Section 3 A Remove the shipping plate from the propeller governor pad as required for governor installation Lubricate the governor shaft splines with engine oil install a new gasket and then install the propeller governor control Attach with plain washers new lock washers and torque the nuts to 204 in lbs Align the spline of the governor drive gear and be sure that the governor is fully seated to the adapter prior to installing the attaching hardware This eliminates the possibility of misalignment Optional accessories such as vacuum pumps hydraulic pumps etc may be installed on the accessory drive pads located on the rear of the accessory housing Remove the accessory drive covers and install new gaskets Install accessories in accordance with the manufacturer s instructions Install all airframe manufacturers required cooling baffles hoses fittings brackets and ground straps in accordance with airframe manufacturer s instructions Chapter 4 Engine Installation a de 3 INSTALLATION OF ENGINE Install per airframe manufacturer s instructions Only the lifting eye bracket installed on the backbone of the crankcase should be used to hoist the engine Consult airframe manufacturer s instructions for engine to airframe connections Remove all protective covers plugs caps and identification
63. eason Superior Air Parts recommends the use of direct sensing flow meters such as vane or turbine styles C Carburetors Carburetors used on Superior Vantage Engines are conventional single barrel float type systems with updraft induction and are equipped with manual throttle and mixture controls In the full lean position the manual mixture control serves as an idle cutoff control The carburetor requires a low pressure engine driven fuel pump supplied Superior Vantage Carbureted Engines require a priming system The engines are supplied with manual primer lines installed to the 1 2 and 4 cylinder inlet ports and plumbing to feed from a common primer source The aircraft priming system should be attached to this common primer source The carburetor system is part of the Superior Vantage Engine and therefore certified as part of the engine No one may make significant changes to either flow settings or mechanical linkages without prior approval by Superior Proper functioning and mixture settings of the carburetor system must be made in flight and ground idle tests These tests should include all envisioned flight attitudes and conditions as well as ground idle temperature variations In addition to performance characteristics exhaust gas and cylinder head temperatures must be monitored during these tests as a means of verifying the correctness of the carburetor system settings March 2004 Superior Air Parts Inc In
64. ecified values per ASTM D 4814 Alabama Arizona Arkansas _ California Colorado Connecticut Delaware Florida Georgia Hawaii Idaho Illinois Indiana lowa Kansas Louisiana Maryland Minnesota Mississippi Montana Nevada New Mexico North Carolina North Dakota Oklahoma Rhode Island South Carolina South Dakota Tennessee Utah Virginia Wisconsin Wyoming Chapter 6 Normal Operating Procedures SUPERIZ A RR PARTS NC WARNING THE USE OF A LOWER OCTANE RATED FUEL CAN CAUSE PRE IGNITION AND OR DETONATION WHICH CAN DAMAGE AN ENGINE THE FIRST TIME HIGH POWER IS APPLIED THIS CAN POSSIBLY CAUSE ENGINE FAILURE THIS WOULD MOST LIKELY OCCUR ON TAKEOFF IF THE AIRCRAFT IS INADVERTENTLY SERVICED WITH THE WRONG GRADE OF FUEL THE FUEL MUST BE COMPLETELY DRAINED AND THE TANK PROPERLY SERVICED PRIOR TO FURTHER ENGINE OPERATION Note For added safety when using 91 Octane motor fuel the use of a Reid Vapor Pressure RVP tester such as a Hodges Volatility Tester which gives a go or no go reading is also recommended March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and 10 360 Series Engines WZ anlage Engine Chapter 6 Normal Operating Procedures E MIS OPERATION INSTRUCTIONS CONTINUED A Preflight Before starting the aircraft engine for the first flight of the day perform a Daily Pre Flight Inspection Refer to Chapter Five Section 5 Daily Pre Flig
65. ed with constant speed propellers or a drop in RPM in installations with fixed pitch propellers The engine may stop if not corrected To avoid this carbureted installations are equipped with a system for preheating the incoming air supply 2 Ground Operation Use of the carburetor air heat on the ground must be held to an absolute minimum and only to verify it is functioning properly On many preheated installations the heated air does not pass through the air filter 3 Take Off All take off and full throttle operations should be made with carburetor heat in the Cold or Off position 4 Climbing When climbing at throttle power settings of 75 or above the carburetor heat control should be set in the Cold or Off position If carburetor heat is necessary it may produce an over rich air mixture When this occurs lean the mixture with the mixture control enough to produce smooth engine operation 5 Cruise Flight During normal cruise flight leave the carburetor air heat control in the Cold position 7 If the presence of carburetor ice is noted apply full carburetor air heat and open the throttle to limiting manifold pressure and or RPM A slight additional drop in manifold pressure which is normal will be noted This will be restored as the ice is melted The carburetor heat control should then be returned to the Cold or Off position March 2004 Superior Air Parts Inc Installation amp
66. ed with two 2 impulse magnetos high tension leads and spark plugs Impulse magnetos provide both a stronger and a retarded spark during low RPM start conditions Superior provides impulse magnetos for both positions to give the best possible start conditions The installation of the engine requires connection of the P lead or grounding lead to the left and right magnetos per the following procedure Attach the ignition P lead terminal to the condenser stud using the lock washer and nut on the magneto Torque the P lead terminal nut to 13 15 inch pounds Attach the P lead ground shield if applicable to the ground screw on the side of the magneto Torque the P lead ground shield screw to 18 20 inch pounds March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and IO 360 Series Engines 16 Ke i anlage Engine The firing order and ignition system wiring diagram for the Superior Vantage Engine is provided in Figure 3 2 B Engine Starting System Superior Vantage Engines are provided with a 12 volt lightweight starter as standard equipment Little is required during installation regarding the starting system except to connect the power wire from the starting relay to the terminal of the starter motor The connection should be torqued to 50 60 inch pounds C Electrical System The specification and installation of an engine driven alternator is the responsibility of the airfr
67. ement of the intake system with respect to hot areas such as exhaust pipes and other engine components Cooler intake air results in better power output and greater service ceilings Intake systems that allow heating of the air reduce available engine power and can reduce service ceilings B Intake Air Requirements and Filtration The intake air and filtration system must be designed for both effective and efficient filtering with minimal flow loss Studies have shown that particulates greater than about 10 microns in size are particularly harmful to engines therefore the filtration system should be selected accordingly Filter manufacturers can provide data regarding effectiveness efficiency and capacity of their products including the effect of particulate size Guidance regarding overall filter size based on filter capacity can be obtained from the filter manufacturer The size of the air filter must also consider the total engine airflow requirements and the maximum air velocity requirements of the filter In general filters are more effective for lower air velocities but practical considerations must be made based on space available Intake air flow requirements of a Superior Vantage Engine are defined in Figure 1 of the Model Specification March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and 10 360 Series Engines N27 i anlage Engine Data Itis recommended that the filter be sized to
68. filter at the carb heat source for several reasons including preventing the risk of filter blockage for alternate air However it is good practice to include a course screen to prevent ingestion of large foreign objects The carb heat air is normally introduced to the induction airstream by means of a mixing box The mixing box includes a baffle door that is manually actuated by the pilot and governs the amount of filtered induction air or carb heat air that is supplied to the carburetor Chapter 3 Aircraft Engine Integration Considerations SUPER IZR R PARTS It is important that the design of the mixing box and damper door minimize pressure drop and turbulence of either filtered intake air or carb heat air Some turbulence is unavoidable in this transition however it is recommended that a straight section of duct be available after the transition to smooth the airflow If possible this section should be a length equivalent to 10 diameters If this length is not possible due to geometry constraints then appropriate steps should be taken to straighten the flow In either case thorough testing should be performed to verify that both intake airflow and carb heat airflow is free of excessive pressure drop and turbulence to the extent that they do not degrade engine performance Good practice also dictates that the mixing box damper door be spring actuated to partially actuate automatically in the event of unexpected a
69. gaskets should be made of corrosion resistant materials such as Inconel or stainless steel and should be designed to withstand the pressure of exhaust backfire events Chapter 3 Aircraft Engine Integration Considerations SUPERIZR R PARTIS 6 LUBRICATION SYSTEM The engine lubrication system is responsible for the reduction in friction between components removal of combustion by products and other contaminants and the removal of heat from internal engine components A continuous supply of clean cooled oil of the proper grade and specification is essential to this process Failure to do so can result in a wide variety of problems ranging from increased wear to engine stoppage A Lubricating Oil Requirements Superior recommends the use of high quality 100 mineral oil during the break in period After engine break in high quality ashless dispersant engine oil per MIL L 22851 or SAE J 1899 should be used in Superior Vantage Engines Ashless dispersant oils are used to prevent the formation of sludge aid in the neutralization of corrosive acids and prevent ash deposits on cylinder walls that can become hot spots and sources for pre ignition The grade or viscosity of oil should be chosen based upon the climate where the engine will be operated as shown in Table 8 1 Superior Vantage Engines are provided with a suction screen filter sometimes referred to as a finger filter to prevent large contaminants from being dr
70. gine March 2004 Superior Air Parts Inc Integration Considerations SUPERIZR Installation amp Operation Manual lt O 360 and 10 360 Series Engines R PARTS 11 ENGINE MOUNTING Superior Vantage Engines are designed for use with a conventional rear four 4 point engine mount Mounting attachment points are provided as part of the engine crankcase and are available for conical or Dynafocal isolator styles Because the engine mount requirements are unique to each airframe application the design of the mount is the responsibility of the airframe manufacturer However the following data is provided for the Vantage Engine to aid in that process A Mount Design and Construction The Superior Vantage Engine is designed for a conventional rear type ring mount Although welded steel tube construction is anticipated due to the benefits in both strength and cost other construction methods are acceptable Considerations during the design of the mount should include in addition to structural strength minimum obstruction to cooling airflow weight WZ i anlage Engine the location and method of installing the oil cooler accessories and accessory cooling and obstruction of intake and exhaust systems Superior Vantage Engines are designed to accommodate modern isolation systems to minimize the vibration levels transmitted to the airframe Both conical and Dynafocal suspension systems are available as identified in the mode
71. h maximum attainable pressure The term maximum attainable pressure as used here refers to an air source that provides maximum intake air pressure including ram air effects while minimizing restrictions and flow losses A reduction in flowrate or total pressure or increased temperature can cause power loss reduced service ceiling and increased possibility of detonation during high power requirements Properly engineered intake systems for naturally aspirated engines should result in total intake air pressures that are greater than ambient air pressure For example air pressure in the intake system can be raised by directing the face of the air pickup into the relative wind of the aircraft Further by locating the air pickup within the propeller diameter ram air effects can be increased Care should be taken to position the air pickup as far as possible away from the propeller axis but within the propeller envelope so as to take advantage of the increased air velocities at the outer areas of the prop Care should also be given to prevent blanking of the intake air pickup by the prop blade Increasing the size of the air pickup particularly in the direction perpendicular to the blade axis can help reduce this potential Care should also be given to designing an air pickup that maintains maximum frontal area during periods of high aircraft angle of attack Typically maximum power is required during flight condition
72. have slack so as to cause delays in response during actuation March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and 10 360 Series Engines 18 WZ i antage Engine 9 Control cables should be the minimum possible length avoiding loops or S turns 10 Control cables should be securely fastened at both ends and at intermediate points to prevent excess vibration and improve responsiveness 11 Superior recommends the use of ball joints or similar apparatus at the lever attachment points to eliminate the potential for binding during actuation B Propeller Control A mechanical control is required to actuate the propeller governor for installations with constant speed propellers The control design should address the same issues as listed above for the throttle and mixture controls C Ignition and Starter Switch An electrical switch or switches must be provided to control each magneto This switch s must be capable of opening and closing the P lead grounding circuit for each magneto and must provide capability to check the operation of each magneto individually An electrical switch must be provided to engage the engine starter Superior recommends that this be a momentary switch to prevent the possibility of leaving the starter engaged for long periods of time Chapter 3 Aircraft Engine Integration Considerations SUPERIZ A RB PART NC D Engine Primer Pr
73. hly clean the aircraft and engine Perform visual inspection H Correct any discrepancies Conduct a normal engine start J Perform a test flight in accordance with Operation Instructions of the O 360 and 10 360 Engine Series Installation and Operation Manual K Correct any discrepancies L Perform a test flight in accordance with airframe manufacturer s instructions M Correct any discrepancies prior to returning aircraft to service N Change oil and filter after 25 hours of operation Chapter 9 Engine Preservation amp Storage N27 antage Engine O 360 SERIES ENGINE MODEL SPECIFICATION DATA APPENDIX A SUPERIZR A IR PAR T LINE SUPERIZR AIR PART Figures oo xoorggme 10 11 12 13 14 Tables Joo ND ch N March 2004 Superior Air Parts Inc Model Specification Data O 360 Series Engine APPENDIX A TABLE OF CONTENTS Induction Airflow Requirements Inter Cylinder Baffle Performance Location of Engine Center of Gravity Horizontal Location of Engine Center of Gravity Vertical O 360 Installation Drawing Front View O 360 Installation Drawing Top View Carburetor Installation Drawing Propeller Load And Full Throttle Curves Altitude Performance At Best Power Cruise Performance Map 80 Power Cruise Performance Map 70 Power Cruise Performance Map 60 Power Fuel Mixture Curve 75 Power Fuel Mixture Curve 65 Power Mini
74. ht Inspection Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i anlage Engine B Starting Procedures The following starting procedures are recommended however the starting procedures for different installations will require some variation from these procedures operator s manual Table 6 1 Normal Starting Procedures Engine Eguipped With Float Type Carburetors 1 Set Carburetor heat control in the Off position 2 Set propeller governor control in the Low Pitch Full RPM position where applicable 3 Turn fuel valves On 4 Move mixture control to Full Rich 5 Turn on Master Switch 6 Turn on Boost Pump if installed 7 Open throttle approximately 4 travel Prime with 1 to 3 strokes of manual priming pump or activate electric primer for 1 to 2 seconds 8 Set magneto selector switch consult airframe manufacturer s handbook for correct position 9 Engage Starter 10 Release starter when engine fires open throttle slightly to keep the engine running If both magnetos are not on switch to Both 11 Check oil pressure gage If minimum oil pressure is not indicated within thirty seconds stop engine and troubleshoot Engines Equipped With Fuel Injectors 1 Set propeller governor control in the Low Pitch Full RPM position where applicable 2 Turn fuel valves On 3 Open throttle approximately Va travel 4 Turn on Master Switch 5 Tu
75. ide engine management information to the pilot The location of the probes is important to the accuracy of their information EGT probes should be located approximately 6 from the exhaust port flange and eguidistant among all cylinders C Exhaust System Materials Exhaust pipes and mounting hardware should be made of corrosion resistant materials such as Inconel or 321 or 347 stabilized stainless steel Other materials such as 304 stainless steel are not siabilized for sustained high temperatures and may result in carbide precipitation and early fatigue failure Wall thickness should be large enough to provide structural integrity yet thin enough to maintain reduced weight Historically some exhaust systems have been made with thicker material to withstand material loss due to scaling and oxidation Proper material selection however has been shown to be a more effective solution allowing for lighter weight exhaust systems March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and 10 360 Series Engines 11 WZ i antage Engine D Exhaust Gaskets Superior recommends the use of metal gaskets in the installation of exhaust systems Metal gaskets improve the seal to the exhaust port reducing the possibility for exhaust gas leakage as well as noise leaks Gaskets also improve the thermal conductivity from the head to the exhaust pipe that helps to remove heat from the exhaust area of the head Exhaust
76. iming of Superior Vantage Engines occurs in two 2 primary ways For fuel injected engines priming is accomplished by momentary actuation of the aircraft boost pump with the mixture control in the full rich position Carbureted engines reguire a manual primer pump that can be actuated by the pilot This primer pump conventionally draws fuel from the fuel line feeding the engine driven fuel pump and feeds the common primer line source at the rear of the engine Figure 1 5 illustrates the common primer line source for a typical Superior Vantage carbureted engine Note Manual primer pumps should include a positive lock feature to prevent the pump from inadvertently actuating during flight March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and 10 360 Series Engines 19 N27 i anlage Engine E Carburetor Heat Control A mechanical control to actuate the carburetor heat mechanism is required for carbureted Superior Vantage Engines The control design should address the same issues as listed above for the throttle and mixture controls F Alternate Air Control A mechanical control is required to actuate the alternate induction air system for fuel injected Superior Vantage Engines The control design should address the same issues as listed above for the throttle and mixture controls Chapter 3 Aircraft Engine Integration Considerations A SUPERIZR R P 10 ENGINE ACCESSORIES Supe
77. in plug and drain oil Replace drain plug torque and safety Remove oil filter Install new oil filter torque and safety Service engine to proper sump capacity with MIL C 6529 Type II oil This oil is not to be used as a lubricant 2 On aircraft Perform a ground run up Perform a pre flight inspection and correct any discrepancies Fly the aircraft for at least one hour or run on ground until 180 F operating temperature is reached Don t exceed 400 F cylinder head temperature 3 On test cell Perform run up to warm engine to operating temperature Run at operating temperature for a minimum of 15 minutes WARNING TO PREVENT POSSIBILITY OF SERIOUS BODILY INJURY OR DEATH BEFORE MOVING THE PROPELLER DO THE FOLLOWING A DISCONNECT ALL SPARK PLUG LEADS March 2004 Superior Air Parts Inc B VERIFY MAGNETO SWITCHES ARE CONNECTED TO MAGNETOS AND THAT THEY ARE IN THE OFF POSITION AND THE P LEADS ARE GROUNDED C THROTTLE POSITIONS CLOSED D MIXTURE CONTROL IDLE CUT OFF E SET BRAKES AND BLOCK AIRCRAFT WHEELS ENSURE THAT AIRCRAFT TIE DOWNS ARE INSTALLED AND VERIFY THAT THE CABIN DOOR LATCH IS OPEN F DO NOT STAND WITHIN THE ARC OF THE PROPELLER BLADES WHILE TURNING THE PROPELLER 4 After operation verify all spark plug leads are removed and remove the top spark plugs Protect the ignition lead ends with AN 4060 Protectors Using a common garden sprayer or equivalent
78. installed in the airframe Therefore the front of the engine is the propeller end and the rear of the engine is the accessory mounting drive area The oil sump is on the bottom of the engine and the cylinder shroud tubes are on the top The terms left and right are defined as being viewed from the rear of the engine looking toward the front Cylinder numbering is from the front to the rear with odd numbered cylinders on the right side of the engine The direction of crankshaft rotation is clockwise as viewed from the rear of the engine looking forward unless otherwise specified Accessory drive rotation direction is defined as viewed from the rear of the engine looking forward 2 CONTINUED AIRWORTHINESS Vantage Engines discussed in this document must be installed and operated in accordance with the limitations conditions and operating procedures described in this document They must also be maintained in accordance with the applicable Overhaul Manual and other Instructions for Continued Airworthiness The engine s time between overhaul TBO period is initially defined as 1000 hours A TBO extension program is in process 3 MODEL DESIGNATIONS The model number designation is defined in a way that the digits of the model number can easily identify the basic configuration of the engine as described in Figure 1 1 10 360 A1A2 Fuel System Type Cylinder Type Crankshaft amp Propeller Ty
79. ir filler blockage due to ice or debris Care should be taken in the design of this mechanism to prevent flutter of the damper door during normal operation in either the filtered air or carb heat mode The mechanism should also be designed to prevent unintended use of carb heat during the filtered air mode including the effects of normal filter blockage That is the automatic spring mechanism should not be designed to be SO sensitive that normal pressure drop due to filler use over time would cause carb heat air to be introduced D Alternate Air Source Fuel injected engines introduce fuel to the induction air at the heated cylinder port and do not present the same concerns regarding induction icing as the carbureted systems However provisions are required to provide an alternate induction air source for fuel injected systems to prevent engine stoppage in the event of filter blockage due to ice or debris As with the design of the carb heat mechanism this is conventionally done by drawing air from the heated lower cowl area and introducing this air downstream from the intake air filter Although it is acceptable to use a mixing box device with flapper door mechanism as with the carb heat apparatus this is not necessary Where the carb heat mixing box must be designed so as to select between the two air sources the alternate air source for fuel injected engines is simply the March 2004 Superior Air Parts Inc Installatio
80. jection at Full Power and Limiting Oil Temperature 16 Appendix B 10 360 Model March 2004 Superior Air Parts Inc Specification Data SUIPER IZR Model Specification Data k EE Engine AIR PARTS INC 10 360 Series Engine Table 5 Oil Pressure Limits Operational Pressures Max Min Idling Normal Operating 95 55 20 Cold 115 Table 6 Engine Accessories i Spark Left Right Fuel Model Carburetor Starter Plug Magneto Magneto Pump Harness 10 360 Unison Unison Precision Aero Acc SkyTec Unison 4371 4371 RSA 5 AF 15473 149 12LS M4001 Table 7 Engine Weight amp Location of Center of Gravity Center of Gravity Weight X Y Z Engine Lb In In In 10 360 Axxx 290 lbs 39 2 69 7 10 10 360 Bxxx 293lbs 44 2 75 7 05 For definition of X Y and Z see figures 3a amp 3b Table 8 Engine Moment of Inertia Moment of Inertia About the Center of Gravity Roll Pitch Yaw Engine Model In Lb Sec In Lbr Sec In Lb Sec 10 360 Axxx 50 2 40 5 64 7 10 360 Bxxx 50 5 49 8 67 4 17 Appendix B 10 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data k EE Engine oe 10 360 Series Engine Table 9 Oil Temperature Limits Minimum for Take off 75 F Maximum Allowable 240 F Recommended Cruising 130 F 200 F Table 10 Fuel Grade Requirements Model Aviation Grade Fuel Minimum Octane Motor Fuel 10 360 91 98 Lead Optional 91 Table 11
81. jector or carburetor may be required by authorized personnel Check fuel lines for dirt or other restrictions Readjustment of fuel injector or carburetor may be required by authorized personnel Tighten all connections Replace damaged parts Clean and gap or replace spark plugs Drain and refill tank with proper grade Clean points Check internal timing of magnetos Check wire with electric tester Replace defective wire Replace connectors on spark plug wire 3 Chapter 7 Abnormal Operating Procedures E MIS 7 LOW OIL PRESSURE ON ENGINE GAGE Installation amp Operation Manual O 360 and 10 360 Series Engines WZ Ken antage Engine Table 7 7 Low Oil Pressure On Engine Gage Probable Cause Lack of oil Air lock or dirty relief valve Leak in line High oil temperature Defective pressure gage Stoppage in oil pump intake passage 8 HIGH OIL TEMPERATURE Correction Add to proper level Clean relief valve Inspect gasket between accessory housing and crankcase See High Oil Temperature in Trouble column Replace defective gage Check line for obstruction Clean suction strainer Table 7 8 High Oil Temperature Probable Cause Insufficient air cooling Insufficient oil supply Low grade of oil Clogged oil lines or strainers Excessive blow by Failing or failed bearing Defective temperature gage 9 EXCESSIVE OIL CONSUMPTION Correction Check air inlet and outlet for deformation
82. l in Full Rich position for rated take off climb and maximum cruise powers above approximately 8096 power In case of a take off from a high elevation airport or during subsequent climb adjust mixture control only enough to obtain smooth operation not for economy 7 Observe instruments for temperature rise Rough operation due to over rich fuel air mixture is most likely to be encountered in carbureted engines at altitudes above 5 000 feet 8 Operate the engine at maximum power mixture for performance cruise power and at best economy mixture for economy cruise power unless otherwise specified in the airplane owner s manual 9 During descent it may be necessary to manually lean carbureted or fuel injected engines to obtain smooth operation March 2004 Superior Air Parts Inc Chapter 6 Normal Operating Procedures SUPERIZR Installation amp Operation Manual Zntage Engine WEST O 360 and 10 360 Series Engines Table 6 8 Leaning with Exhaust Gas Temperature Gage Normally aspirated engines with fuel injectors or carburetors Maximum Power Cruise above Best Economy Cruise 80 power Superior Vantage approximately 80 power and Engines should not be leaned below Do not lean below peak when operating above 80 EGT on carbureted engines Do not power lean beyond 50 F lean of peak on fuel injected engines Table 6 9 Leaning with Flowmeter Lean to applicable fuel flow values Because of air fuel mixture va
83. l listing of Chapter 1 Dynafocal suspension systems are designed to minimize the dynamic coupling of the installation and therefore result in minimal vibration levels transmitted to the airframe structure Lord Manufacturing Company has developed this technology and provides isolator components The Superior Vantage Engines are designed to accommodate the Lord mounts for conical as well as 1 Dynafocal and 2 Dynafocal suspension styles Table 3 2 lists the Lord Mounting Kit part number for the Superior Vantage Engine mount options Table 3 2 Lord Engine Mounts for Superior Vantage Engines Superior Vantage Mount Style Engine Model Series O IO 360 x1xx 1 Dynafocal O IO 360 x2xx 32 Dynafocal O IO 360 x3xx Conical 22 March 2004 Superior Air Parts Inc Figure Lord Mounting Kit Part Number as J 9613 40 3 5 3 6 J 6230 1 Chapter 3 Aircraft Engine Integration Considerations SUPERIZR Installation amp Operation Manual poc Engine AIR PARTS INC O 360 and 10 360 Series Engines NOTE DIMENSIONS FOR REFERENCE ONLY Figure 3 4 1 Dynafocal Mount Dimensions NOTE DIMENSIONS FOR REFERENCE ONLY Figure 3 5 2 Dynafocal Mount Dimensions 23 Chapter 3 Aircraft Engine March 2004 Superior Air Parts Inc Integration Considerations SUPERIZ A ER Rak EES NC Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i anlage Engine Figure 3
84. ld lt 30 F SAE 30 or 10W30 Standard 30 90 F SAE 40 Hot gt 60 F SAE 50 Notes 1 For Break In Operation see Chapter 5 3 A straight mineral oil meeting MIL L 6082 should be used After Break In Ashless Dispersant Oils meeting MIL L 22851 or SAE J 1899 are to be used 2 Semi Synthetic Oils may be used after break in provided that they meet MIL L 22851 or J 1899 Table 8 2 Oil Sump Capacity Maximum Oil Capacity 8 U S Quarts Minimum Safe Quantity in the sump 2 5 U S Quarts March 2004 Superior Air Parts Inc Chapter 8 Servicing Requirements SUPERIZ AUR Bac ETS NC 3 FUELS Superior Vantage Engines are certified for 100LL Avgas per ASTM D910 91 98 lead optional Avgas per ASTM D910 and Motor Gasoline with a minimum antiknock index R M 2 method of 91 per ASTM D4814 Minimum octane fuels are listed in Table 8 3 A The minimum aviation fuel grade is 91 98 Octane Avgas lead optional Under no circumstances should aviation fuel of a lower octane rating be used B 91 Octane Motor Fuel The Vantage series engine can operate and perform at a rated power with unleaded automotive fuel without alcohol of at least 91 Octane When operating with unleaded automotive fuel use only 91 minimum octane premium grade fuel Table 8 3 Minimum Octane Fuels Minimum Octane Aviation Grade Motor Fuel 91 98 Avgas 91 R M 2 Lead Optional No Alcohol March 2004 Superior Air Parts Inc Install
85. levation pressure altitude 3 Warm up at approximately 1 900 2 100 RPM with rotor engaged in accordance with manufacturer s instructions until all systems are properly warmed 4 Engine is warm enough for take off when the oil temperature exceeds 75 F and the engine does not hesitate with throttle advancement March 2004 Superior Air Parts Inc Chapter 6 Normal Operating Procedures SUPERIZR Installation amp Operation Manual entage Engine HU as O 360 and 10 360 Series Engines E Pre Takeoff Ground Check Table 6 5 Fixed Wing Pre Takeoff Ground Check 1 Warm up as stated above in Table 6 3 2 Mixture control Full Rich check oil pressure and oil temperature 3 Propeller Check Cycle the propeller through its complete operating range to check operation and return to full low pitch position Full feathering check on a twin engine aircraft on the ground is not recommended but the feathering action can be checked by running the engine between 1000 1500 RPM then momentarily pull the propeller control into the feathering position Do not allow the RPM to drop more than 500 RPM 4 Magneto Check Factors other than the ignition system affect magneto drop Some factors include load power output and mixture strength Make the magneto check in accordance with the following procedures CAUTION ABSENCE OF RPM DROP WHEN CHECKING MAGNETOS MAY INDICATE A MALFUNCTION IN THE IGNITION CIRCUIT SHOULD THE PROPELLER BE MOVED BY
86. ltiplying HPs by the square root of the temperature ratio adjusting for absolute or Rankine temperature Thus 139x 460 50 460 75 0 5 135 7 HP actual EE eg n M 24 S po p eR s n PE Sea Level Performance LevelPerformance Limiting manifold Koss Le I EE EE EF E Pressure Altitude Ft x 1000 Absolute Dry Manifold Pressure In Hg eee EE Ed See EES ES SE EE eg DE ZA Power Hp Figure 8 Altitude Performance At Best Power 9 Appendix B 10 360 Model March 2004 Superior Air Parts Inc Specification Data SUIPER IZR Model Specification Data p m Engine AIR PARTS ING 10 360 Series Engine Cruise Performance Superior Vantage O IO 360 Series 80 Power 144 Hp Rich of Peak Operation CL EE No ne 2200 rt LL Motor Gasoline UN FEN B 430 F CHT MIT E Je J Lp 30 N e N o Wa EE EE Peak EGT is 5 ES gt N EN No with Motor Gasoline Above 500 F CHT BG SC e 6 58 60 62 64 66 6 8 70 72 74 76 78 94 Fuel Flow Lb Hr N o Absolute Dry Manifold Pressure In Hg N o 24 5 Figure 9 Cruise Performance Map 80 Power 10 Appendix B 10 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data a RE 10 360 Series Engine Cruise Performance Superior Vantage O IO 360 Series 70 Power 126 Hp Rich of Pe
87. m 17 Chapter 3 Aircraft Engine March 2004 Superior Air Parts Inc Integration Considerations SUPERIZR R PARTIS 9 ENGINE CONTROLS Some manually operated controls are required to operate a Superior Vantage Engine These include mechanical controls electrical controls and fuel controls A Throttle and Mixture Control Mechanical controls are required to actuate the throttle and mixture levers for both carbureted and fuel injected Superior Vantage Engines Many methods may be used to accomplish this as long as the following issues are addressed 1 Individual controls are supplied for throttle and mixture levers 2 The control allows the throttle lever to contact the idle stop screw 3 The control allows the throttle lever to reach full open 4 The control allows the mixture lever to contact the idle cutoff stop 5 The control allows the mixture lever to reach full rich 6 Superior recommends that the full open throttle position and full rich mixture position be limited by the forward motion of the control and not the lever touching the stop on the carburetor or fuel injector servo This is to prevent binding and excessive compression within the control itself should the lever hit its stop before the control hits it full forward potential 7 Superior recommends a vernier style mixture control for improved control during leaning 8 The control does not bind or
88. mum Oil Quantity Maximum Fuel Flow Requirements Fuel Filter Requirements Fuel Pump Inlet Pressure Limits Oil Heat Rejection Airside Heat Rejection Crankcase Pressure Oil Pressure Limits Engine Accessories Engine Weight amp Location of Center of Gravity Engine Moment of Inertia Oil Temperature Limits Fuel Grade Requirements Operating Conditions Accessory Temperature Limits N27 anlage Engine Page Number O O1 N Appendix A O 360 Model Specification Data SUIPER IZR Model Specification Data k EE Engine AIR PARTS INC O 360 Series Engine Induction Air Flow Superior Vantage O 10 360 Series Air Flow Lb Min EE E EE eo D O See ae 1900 2000 2100 2200 2300 2400 2500 2600 2700 2800 Engine Speed RPM Figure 1 Induction Air Flow Requirements 1 Appendix A O 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data k PE eo a O 360 Series Engine Inter Cylinder Baffle Performance Superior Vantage O IO 360 Series 2500 2000 1500 1000 Cooling Air Flow Lb min 500 4 0 4 5 5 0 5 5 6 0 6 5 7 0 7 5 8 0 Baffle Differential Pressure In H50 Figure 2 Inter Cylinder Baffle Performance 2 Appendix A O 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data rise tahan e O 360 Series Engine
89. n Cooling Nozzle To Prop Governor If installed Figure 3 1 Oil System Schematic 14 Chapter 3 Aircraft Engine March 2004 Superior Air Parts Inc Integration Considerations A 7 PROPELLER ATTACHMENT The flange for attaching the propeller to the crankshaft is a modified SAE Type 2 Propeller Flange per AS127 with 1 2 bolts The nut and bolt specifications torque specs and methodology size and use of safety wire etc are to be specified by the propeller manufacturer March 2004 Superior Air Parts Inc 15 SUPERIZR Installation amp Operation Manual Vantage Engine een em O 360 and IO 360 Series Engines Chapter 3 Aircraft Engine Integration Considerations SUPERIZR R PARTIS 8 ELECTRICAL SYSTEM The engine electrical system is responsible for three 3 primary duties They are ignition starting and power supply to the aircraft Superior Vantage Engines are supplied with two 2 magnetos that have been properly timed at the factory as well as an engine starter Other than electrical connections little is required in terms of installation design for the ignition or starting systems Alternators are not provided for Superior Vantage Engines due to the variation in requirements from one airframe to another Specification of an alternator and its connection to the airframe electrical system is the responsibility of the installation design A Ignition System Superior Vantage Engines are suppli
90. n amp Operation Manual O 360 and IO 360 Series Engines N27 i anlage Engine availability of alternate air Therefore it is not necessary to block off the normal filtered air source Like the carb heat mechanism the alternate air source should be designed to minimize both flow losses and turbulence An entrance area at least 75 of the fuel injector servo area is recommended as well as provisions to straighten the flow after introduction to the intake air duct A screen to prevent ingestion of large foreign objects may be necessary The alternate air source mechanism should be manually controllable by the pilot As with the carb heat mechanism it is advised that the alternate air source be spring actuated so it will partially actuate automatically in the event of unexpected air filter blockage due to ice or debris The mechanism should be designed to preclude flutter and unintended operation during the filtered air mode including the effects of normal filter blockage The automatic spring mechanism should not be designed to be so sensitive that normal pressure drop due to filter use over time would cause carb heat air to be introduced E Backfire Tolerance The induction system carb heat mechanism and alternate air source must be designed to withstand normal induction backfire events without structural failure or fire Chapter 3 Aircraft Engine Integration Considerations A IS 3 FUEL SY
91. n Procedures 4 Returning An Engine To Service After Storage Appendix A O 360 Model Specification Data Appendix B 10 360 Model Specification Data March 2004 Superior Air Parts Inc N27 i antage Engine RAR G G GQ N N D D Q N N SUPERIZR Installation amp Operation Manual L s Engine M O 360 and 10 360 Series Engines Manual Number SVIOMO 1 Revision History Revision Effectiv Description Pages Letter e Revised Date A 03 29 04 Initial Release All WARNING It is the users responsibility to insure that this is the current revision of this manual Do not perform any operation installation maintenance or other procedure until confirming this manual is current March 2004 Superior Air Parts Inc SUPERIZ Installation amp Operation Manual Zntage Engine O 360 and 10 360 Series Engines List Of Figures Figure Figure Description Chapter Page Number 1 1 Model Number Designation 1 1 1 2 O 360 Engine Front View 1 5 1 3 O 360 Engine Left Side View 1 6 1 4 O 360 Engine Top View 1 7 1 5 O 360 Engine Rear View 1 8 1 6 10 360 Engine Front View 1 9 1 7 10 360 Engine Left Side View 1 10 1 8 IO 360 Engine Top View 1 11 1 9 10 360 Engine Rear View 1 12 3 1 Oil System Schematic 3 14 3 2 Ignition Wiring Diagram 3 17 3 3 Alternator Mounting Pad 3 21 3 4 1 Dynafocal Mount Dimensions 3 23 3 5 2 Dynafocal Mount Dimensions 3 23 3 6 Conical Mount Dimensions 3 24 3 7 Limit and Ultimate E
92. nd parallel to the crankshaft The camshaft actuates hydraulic lifters that operate the valves through push rods and valve rockers Crankcase The crankcase is made from aerospace grade AA C355 T71 stabilized structural aluminum alloy per AMS 4214 The assembly consists of two reinforced aluminum alloy castings fastened together by means of studs bolts and nuts The main bearing bores are machined for use with precision type main bearing inserts Accessory Housing The accessory housing is made from an aluminum casting and is fastened to the rear of the crankcase and the top rear of the sump Oil Sump The sump incorporates an oil drain plug oil suction screen mounting pad for carburetor or fuel injector the intake riser and intake pipe connections Cylinders Millennium Cylinders are used exclusively These air cooled cylinders are manufactured by screwing and shrinking the two major parts head and barrel together The heads are made from AMS 4220 aluminum alloy casting material All barrels are made from forgings produced to AMS 6382 forging specifications They are internally choked and honed to allow optimal operating conditions for the rings and pistons at operating temperatures March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and IO 360 Series Engines 13 WZ i anlage Engine Pistons The pistons are made from an aluminum alloy The piston pin is a full floating type
93. ng air between and around the barrels and cylinder heads as controlled by the inter cylinder baffles The amount of airflow over the engine is controlled by the pressure differential between the upper and lower cowl volumes Figure 2 of the Model Specification Data provides detailed information concerning the mass airflow as a function of pressure differential over a Superior Vantage Engine Superior Vantage Engines are tested and calibrated for airside heat rejection on highly instrumented test stands Table 4 of the Model Specification Data defines cooling airflow requirements as a function of power output Chapter 3 Aircraft Engine Integration Considerations SUPERIZR R PARTIS C Oil Heat Rejection Engine oil is the other primary means of cooling the engine Cooling of the engine oil occurs partly through heat transfer through the walls of the crankcase and oil sump and partly through a supplemental oil cooler Supplemental oil coolers are oil to air heat exchanger designs and draw cooling air from the upper cowl plenum area as discussed previously Oil heat rejection requirements for Superior Vantage Engines are defined in Table 4 of the Model Specification Data Superior Air Parts recommends that the oil cooler be sized to provide at least 150 of the required maximum heat transfer to provide an adequate margin of safety The reduction in temperature and density of the ambient air with increasing altitude can signifi
94. ngine Page Number O O1 N Appendix B 10 360 Model Specification Data SUIPER IZR Model Specification Data k EE Engine AIR PARTS INC 10 360 Series Engine Induction Air Flow Superior Vantage O IO 360 Series Air Flow Lb Min EE EY EE DI ER D O See ee 1900 2000 2100 2200 2300 2400 2500 2600 2700 2800 Engine Speed RPM Figure 1 Induction Air Flow Requirements 1 Appendix B 10 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data k PE dites EH 10 360 Series Engine Inter Cylinder Baffle Performance Superior Vantage O IO 360 Series 2500 2000 1500 1000 Cooling Air Flow Lb min 500 4 0 4 5 5 0 5 5 6 0 6 5 7 0 7 5 8 0 Baffle Differential Pressure In H50 Figure 2 Inter Cylinder Baffle Performance 2 Appendix B 10 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZ Model Specification Data Vista score e 10 360 Series Engine o N Figure 3a Location of Engine Center of Gravity Horizontal 3 Appendix B 10 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZ Model Specification Data Vitae score e 10 360 Series Engine Figure 3b Location of Engine Center of Gravity Vertical 4 Appendix B 10 360 Model March 2004 Superior Air Parts
95. ngine Forces 3 26 3 8 Engine Mount Forcing Function for Engine Startup and Shutdown 3 27 3 9 Engine Mount Forcing Function for Steady State Conditions 3 27 March 2004 Superior Air Parts Inc SUPERIZR PARTS Table Number 1 1 1 1 1 1 1 1 D Po O O GQ O O G Go W l O O1 GQ N G N G o 1 NN Installation amp Operation Manual O 360 and IO 360 Series Engines List Of Tables Table Description Manufacturer s General Specifications Manufacturer s Physical Specifications Views of the Engine Accessory Drive Data Lord Engine Mounts for Superior Vantage Engines Limit and Ultimate Engine Mount Loads Instrumentation Connections Normal Starting Procedures Starting A Flooded Engine Ground Running Fixed Wing Warm Up Ground Running Rotorcraft Warm Up Fixed Wing Pre Takeoff Ground Check Rotorcraft Pre Takeoff Ground Check Fuel Mixture Leaning General Rules Leaning with Exhaust Gas Temperature Gage Leaning with Flowmeter Leaning with Manual Mixture Control Shut Down Procedure Abnormal Operating Procedures Engine Will Not Start Rough Idling Engine Not Able To Develop Full Power Rough Engine Operation Low Power amp Engine Runs Rough Low Oil Pressure On Engine Gage High Oil Temperature Excessive Oil Consumption Oil Grades Oil Sump Capacity Minimum Octane Fuels Consumables March 2004 Superior Air Parts Inc Chapter O
96. omponents of the alternator However depending upon the power output of the alternator and the installation design additional cooling may be required Supplemental cooling may easily be provided through the use of blast tubes to direct ram air to a specific area s of the alternator Care should be given during the design of blast tubes that they do not inadvertently degrade the airflow to other areas of the engine or installation E Propeller Governor An AND20010 drive pad is provided for the installation of an engine driven propeller governor The mounting pad includes lubricating holes to provide engine oil to and from the governor for internal lubrication Table 3 1 Accessory Drive Data Accessory Starter Alternator not supplied Tachometer Vacuum Pump Propeller Governor Fuel Pump Plunger Operated Drive Direction of Rotation Ratio 16 556 1 Counter Clockwise 3 250 1 Clockwise 0 500 1 Clockwise 1 800 1 Counter Clockwise 0 866 1 Clockwise 0 500 1 Reciprocating Note Direction of rotation for accessories is listed as viewed from the rear of the engine March 2004 Superior Air Parts Inc 20 Chapter 3 Aircraft Engine Integration Considerations SUPERIZR Installation amp Operation Manual Vain Engine WE O 360 and 10 360 Series Engines CRANKCASE Cows SIDEVIEW MOUNTING PAD Figure 3 3 Alternator Mounting Pad 21 Chapter 3 Aircraft En
97. ormal Operating Procedures SUPERIZR Installation amp Operation Manual Zatage Engine ae ee O 360 and 10 360 Series Engines A R P F Operation In Flight Note See airframe manufacturer s instructions for recommended power settings and limits Note Move the controls slowly and smoothly Table 6 7 Fuel Mixture Leaning General Rules 1 Improper fuel air mixture during flight is a contributing factor to engine problems particularly during elevated take off and climb power settings The procedures described in this manual provide proper fuel air mixture when leaning Vantage engines It is therefore recommended that operators of all Vantage engines utilize the instructions in this publication any time the fuel air mixture is adjusted during flight 2 Manual leaning may be monitored by exhaust gas temperature indication fuel flow indication and by observation of engine speed and or airspeed Regardless of the instruments used in monitoring the mixture the following general rules should be observed by the operator of Superior Air Parts aircraft engines 3 Never exceed the maximum red line cylinder head temperature limit of 500 F 4 For maximum service life cylinder head temperatures should be maintained below 430 F during high performance cruise operation and below 400 F for economy cruise powers 5 Do not lean engines with automatically controlled fuel systems 6 On engines with manual mixture control maintain mixture contro
98. pe Power Rating Accessory Package Crankcase amp Engine Mount Type Figure 1 1 Model Number Designation March 2004 Superior Air Parts Inc Chapter 1 Engine Description SUIPER IZ Installation amp Operation Manual eim Engine AIR PARTS INC O 360 and 10 360 Series Engines Fuel System Type IO Denotes Port Fuel Injection System and opposed cylinder arrangement O Denotes a carbureted system and opposed cylinder arrangement Cylinder Type 360 Parallel valve cylinder 361 cubic inches Model Suffix Denotes detail engine configuration 1 Digit Crankshaft amp Propeller Type A Fixed Pitch Thin wall front main B Constant Speed Thin wall front main 2 Digit Crankcase amp Engine Mount Type 1 311 Dynafocal Mount 2 32 Dynafocal Mount 3 Conical Mount 3 Digit Accessory Package Ignition System Fuel System Carbureted Fuel Injected A Unison Magnetos Precision Carburetor Precision Fuel Injection 4 Digit Power Rating Piston Compression Ratio Cylinder Type 360 CR HP i 2 8 5 180 For Future Use March 2004 Superior Air Parts Inc Chapter 1 Engine Description SUPERIZR R PARTIS 4 ENGINE COMPONENTS GENERAL DESCRIPTION The O 360 and 10 360 series engines are air cooled four cylinder horizontally opposed direct drive engines See Table 1 1 for Manufacturer s General Specifications A The complete engine includes the following components and assemblies oO EO O
99. position and note RPM The difference between the two magnetos operated individually should not differ more than 25 75 RPM with a maximum drop for either magneto of 150 RPM Slight engine roughness is expected during this test However excessive roughness may indicate spark plug fouling or other ignition system problem Note Minor spark plug fouling can usually be cleared with magnetos on and holding throttle at 2200 RPM 6 Mixture Move toward idle cutoff until RPM peaks and hold for ten seconds Return mixture to full rich March 2004 Superior Air Parts Inc Chapter 6 Normal Operating Procedures SUIPER IZ Installation amp Operation Manual warisu Engine AIR PARTS INC O 360 and 10 360 Series Engines Table 6 6 Rotorcraft Pre Takeoff Ground Check 1 Warm up as stated above in Table 6 4 2 Mixture control Full Rich check oil pressure and oil temperature 3 Magneto Check Raise collective pitch control to obtain 15 inches of manifold pressure and 2 000 RPM Switch from both magnetos to one and observe drop off switch back to both until the engine regains its speed and then switch to the other magneto and note drop off At no time should this drop off exceed 175 RPM Difference between the drop offs of the two magnetos should never exceed 50 RPM If a smooth drop off past normal is observed it is usually a sign that the mixture is either too lean or too rich March 2004 Superior Air Parts Inc Chapter 6 N
100. propeller in Low Pitch setting 4 Operate at approximately 1000 1200 RPM for at least one minute in warm weather and as required during cold weather to prevent cavitation in the oil pump and to assure adequate lubrication Avoid prolonged idling and do not exceed 2200 RPM on the ground 5 Advance throttle slowly until tachometer indicates an engine speed of approximately 1200 RPM Allow additional warm up time at this speed depending on ambient temperature This time may be used for taxiing to takeoff position The minimum allowable oil temperature for run up is 75 F CAUTION DO NOT OPERATE THE ENGINE AT RUN UP SPEED UNLESS OIL TEMPERATURE IS 75 F MINIMUM AND OIL PRESSURE IS WITHIN SPECIFIED LIMITS OF 50 95 PSI CAUTION OPERATION OF THE ENGINE AT HIGH RPM BEFORE REACHING MINIMUM OIL TEMPERATURE MAY CAUSE LOSS OF OIL PRESSURE AND ENGINE DAMAGE 6 Perform all ground operations with cowling flaps if installed fully open and propeller control set for maximum RPM except for brief testing of propeller governor if so equipped 7 Restrict ground operations to the time necessary for warm up and testing 8 Engine is warm enough for take off when the oil temperature exceeds 75 F and the engine does not hesitate with throttle advancement Table 6 4 Ground Running Rotorcraft Warm Up 1 Head the aircraft into the wind 2 Leave mixture control Full Rich for the entire warm up period This setting is dependent upon field e
101. provide a minimum of 150 of this flow to minimize pressure drop for both clean and dirty filters C Carburetor Heat Due to the cooling effects of both fuel vaporization and airflow through the venturi carburetor ice can form with outdoor air temperatures as high as 100 F Therefore it is necessary to provide a mechanism to introduce heat to the intake airstream downstream of the air filter to prevent this condition and to correct it if icing were to occur This mechanism also serves the purpose of an alternate air source should the filter become unexpectedly blocked due to ice or debris The minimum temperature rise required of the carb heat mechanism is specified in the FARs The design of the carb heat system should in general follow the same guidelines as the induction air system to minimize pressure loss and turbulence For example the flow area should be as large as possible to reduce air velocity and therefore flow losses Relatively slow moving air across a heat source will also experience a higher temperature rise than faster moving air over the same heat source Good practice suggests that the carb heat duct should be at least 75 the size of the carburetor inlet The air source for the carb heat mechanism should be from a source other than the standard filtered intake air It is common for the carb heat air to be drawn from within the lower cowl area Itis also conventional to omit the use of a traditional air
102. r ae Crankcase Assembly Crankshaft Assembly Camshaft Assembly Valve Train Assembly Cylinder Assemblies Connecting Rod Assemblies Oil Sump Assembly Inter Cylinder Baffles Starter 10 Lubrication System includes oil filter 11 Accessory Drive 12 Ignition System includes spark plugs Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i anlage Engine 13 Fuel System 14 Starter Support Assembly 15 Oil Gage 16 Induction System 17 Accessories Note Complete engine does not include outer cylinder baffles propeller governor and airframe to engine control cables attaching hardware hose clamps vacuum pump exhaust system fittings or alternator B Specifications The manufacturers physical specifications are listed in Table 1 2 are applicable to the O 360 and 10 360 series engines See Model Specification Data MSD for more specific information Table 1 1 Manufacturer s General Specifications Model Rated Power Hp Rated Speed RPM RPM Bore inches In Stroke inches In Displacement cubic inches In Compression Ratio Firing Order Spark timing BTDC Propeller drive ratio Propeller drive rotation viewed from rear 3 March 2004 Superior Air Parts Inc O 360 and 10 360 180 2700 5 125 4 375 361 0 8 5 1 1 3 2 4 25 1 1 Clockwise Chapter 1 Engine Description SUIPER IZ Installation amp Operation Manual QD Engine AIR PARTS INC O 360 and 10 360
103. r is noted continue draining until only clean fuel appears 8 Make sure all shields and cowling are secure and in place If missing or damaged repair or replacement should be made before the aircraft is flown 9 Check controls for general condition security and freedom of travel and operation 10 Induction system air filter should be inspected and serviced in accordance with the airframe manufacturer s recommendations Chapter 5 Special Procedures A SUPERIZR R P Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i anlage Engine CHAPTER 6 Normal Operating Procedures 1 GENERAL This section has the necessary procedures to operate the O 360 and IO 360 series engines Complying with these instructions will optimize life economy and operation of the Vantage series engines Note The following operator instructions do not constitute a complete aircrafts operator s instructions and applies to the engine only Refer to the airframe manufacturer s instruction for additional information 2 ENGINE OPERATION AND LIMITS Data for the following limits may be found in the Model Specification Data in the appropriate Appendices These Engine Operational Limits should be reviewed by the operator prior to any initial operations of the O 360 or 10 360 Engine Series A Propeller Load and Full Throttle Curve B Altitude Performance at Best Power C Cruise Performance Maps D Fuel
104. riations on carbureted engines this is recommended for fuel injected engines only unless otherwise recommended by airframe manufacturer Table 6 10 Leaning with Manual Mixture Control Economy cruise 80 power or less without flowmeter or EGT gage Carbureted Engines Fuel Injected Engines Slowly lean mixture control from Full Slowly lean mixture control from Rich position Full Rich position Lean until engine roughness is noted Continue leaning until slight loss of power is noted and or is accompanied by roughness Enrich until engine runs smoothly Enrich until engine power is Slight additional enrichment is regained and or runs smoothly recommended to ensure adequate Slight additional enrichment is performance recommended to ensure adequate performance Table 6 11 Shut Down Procedure 1 Set propeller governor control to Low Pitch High RPM when applicable 2 Idle until there is a definite reduction in cylinder head temperature 3 Move mixture control to Idle Cut Off 4 When engine stops turn off switches Omit step one for Rotorcraft shut down March 2004 Superior Air Parts Inc Chapter 6 Normal Operating Procedures SUPERIZR R PARTIS G Use of Carburetor Heat Control 1 Under certain damp atmospheric conditions and temperatures of 20 F to 100 it is possible for ice to form in the induction system A loss of power is reflected by a drop in manifold pressure in installations equipp
105. rior Vantage Engines are provided complete with several accessories Provisions are available for mounting and driving of additional accessories whose specification is more installation dependent A Supplied Accessories Superior Vantage Engines are supplied with several accessories as specified in Table 6 of the Model Specification Data 1 Lightweight starter 2 Two 2 magnetos with impulse couplings 3 Engine driven fuel pump 4 Propeller governor adapter if so equipped 5 Full flow oil filter 6 Spark Plugs amp Ignition Harness 7 Fuel System Carburetor or Fuel Injection B Accessory Drive Data Table 3 1 lists the drive data for the accessories C Accessory Vacuum Pump An AND20000 drive pad is provided for the installation of an engine driven vacuum pump or alternator The mounting pad includes lubricating holes to provide engine oil to and from the vacuum pump for internal lubrication Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i anlage Engine D Alternator A mounting pad is provided for an alternator on the front of the crankcase with 5 16 18UNCF x 0 7 tapped holes as shown in Figure 3 3 This mounting pad and the V belt drive pulley on the flywheel are designed to accept standard front pulley general aviation alternators The V belt and pulley are SAE Size 0 380 in accordance with SAE J636 Typically these alternators include a fan to cool the internal c
106. rn on Boost Pump 6 Open throttle to wide open Move mixture control to Full Rich uniil a slight but steady fuel flow is noted approximately 3 to 5 seconds Return mixture control to Idle Cut off 7 Set magneto selector switch consult airframe manufacturer s handbook for correct position 8 Engage Starter 9 Release starter when engine fires If both magnetos are not on switch to Both 10 Move mixture control slowly and smoothly to Full Rich and retard the throttle to desired idle speed 11 Check oil pressure gage If minimum oil pressure is not indicated within thirty seconds stop engine and troubleshoot HOT STARTS USE THE SAME PROCEDURE AS A NORMAL START WITH THE EXCEPTION OF PRIMING OMIT PRIMING March 2004 Superior Air Parts Inc Chapter 6 Normal Operating Procedures Refer to your airframe SUIPER IZ Installation amp Operation Manual Sol Engine AIR PARTS INC O 360 and 10 360 Series Engines Table 6 2 Starting A Flooded Engine 1 Set mixture control to IDLE CUT OFF 2 Set throttle to 1 2 open 3 Turn Magneto start switch to START 4 When engine starts return the magneto start switch to BOTH Retard the throttle and slowly advance the mixture control to FULL RICH position C Cold Weather Starting During extreme D Ground Run and Warm Up The engines cold weather below freezing it may be covered in this manual are air cooled and necessary to preheat the engin
107. rs are sprayed Stop crankshaft with none of the pistons at top dead center 5 Re spray each cylinder To thoroughly cover all surfaces of the cylinder interior move the nozzle or spray gun from the top to the bottom of the cylinder 6 Install dehydrator plugs MS27215 2 or AN4062 1 in each of the upper spark plug holes Make sure each plug is blue in color when installed 7 Before engine has cooled install desiccant bags in exhaust pipes Attach a red Remove Before Flight streamer to each bag of desiccant in the exhaust pipes and seal the openings 8 Seal all engine openings exposed to the atmosphere using suitable plugs and covers 9 On aircraft tag each propeller in a conspicuous place with the following notation on the tag or if new or overhauled on the propeller flange Do Not Turn Propeller Engine Preserved Preservation Date 3 INSPECTION PROCEDURES A Aircraft prepared for indefinite storage must have the cylinder dehydrator plugs visually inspected every 15 days The plugs must be changed as soon as they indicate other than a dark blue color If the dehydrator plugs have changed color in one half or more of the cylinders all desiccant material on the engine must be replaced B The cylinder bores of all engines prepared for indefinite storage must be re sprayed with corrosion preventive mixture every 90 days Chapter 9 Engine Preservation amp Storage A IS 4 RETU
108. s having high angle of attack and reductions in airflow will restrict maximum power capability The intake air system should be designed to minimize pressure and flow losses Sharp elbows and abrupt duct expansions or contractions all contribute to system losses Changes in duct sizing should be accompanied by tapered transitions to minimize these losses Duct losses are a function of air velocity and can Chapter 3 Aircraft Engine Integration Considerations SUPERIZR P BA BTS be significantly reduced by increasing duct size and thereby reducing the air velocity Utilizing ducts with circular cross sections or square cross sections with the highest possible aspect ratio can also reduce duct losses Turning vanes can be used to reduce losses in sharp corners when necessary The state of the airflow as it enters the carburetor or fuel injector servo body is critical to effective and efficient fuel mixing Both carburetor and fuel injector servo bodies sense mass airflow and introduce fuel based on that measurement If the airflow is turbulent during this process inaccurate airflow sensing can occur resulting in improper fuel flow Turbulence of the intake air in a carbureted system will also promote poor fuel air mixing and large cylinder to cylinder mixture variations The consequences of these conditions can be as simple as reduced power or as great as in cylinder detonation Care should also be given to the plac
109. stallation amp Operation Manual O 360 and 10 360 Series Engines WZ i antage Engine D Fuel Injection Systems Port Type Fuel injector systems used on Superior Vantage Engines are direct port injection systems with a fuel metering servo at the entrance to the intake manifold The fuel metering servo is equipped with manual throttle and mixture controls In the full lean position the manual mixture control serves as an idle cutoff control The fuel injection system requires a high pressure engine driven fuel pump supplied Superior Vantage Fuel Injected Engines do not require a separate priming system Priming is accomplished by operating an aircraft boost pump with the manual mixture control in the full rich position After priming the manual mixture control should be moved to the idle cutoff position for engine start and then moved back to full rich after the engine has started Proper functioning and mixture settings of the fuel injection system must be made in flight and ground idle tests These tests should include all envisioned flight attitudes and conditions as well as ground idle temperature variations In addition to performance characteristics exhaust gas and cylinder head temperatures must be monitored during these tests as a means of verifying the correctness of the fuel injection system settings Chapter 3 Aircraft Engine Integration Considerations SUPERIZ A E Fuels Superior Vantage Engines
110. ta k PE hi O 360 Series Engine Minimum Oil Quantity Superior Vantage O IO 360 Series Oil Quantity U S Quarts 30 20 10 0 10 20 30 Engi Engi ice Roll Angle Deg Right Figure 14 Minimum Oil Quantity 15 Appendix A O 360 Model March 2004 Superior Air Parts Inc Specification Data SUPERIZR Model Specification Data Tia Engine O 360 Series Engine Table 1 Maximum Fuel Flow Requirements Max Rich Fuel Flow Required Pounds Per Hour O 360 108 Table 2 Fuel Filter Requirements 100 Mesh Screen 0 005 Max Particle Size Table 3 Fuel Pump Inlet Pressure Limits Minimum PSIG Maximum PSIG O 360 40 5 8 Table 4 Oil Heat Rejection Airside Heat Rejection Crankcase Pressure US Typical 1 450 BTU Minute Oil Heat R t AMEDEO Maximum 2 1000 BTU Minute me 1800 Ft Min Sea Level Minimum Cylinder Cooling Airflow Drop Recommended UU Gn 6 5 In H2O Baffle Press Drop Crankcase Pressure Maximum 4 0 In H O Notes 1 Typical Heat Rejection In Cruise 2 Maximum Heat Rejection at Full Power and Limiting Oil Temperature 16 Appendix A O 360 Model March 2004 Superior Air Parts Inc Specification Data SUIPER IZR Model Specification Data k EE Engine AIR PARTS INC O 360 Series Engine Table 5 Oil Pressure Limits Operational Pressures Max Min Idling Normal Operating 95 55 20 Cold 115 Table 6 Engine Accessories i Spark Left Right Fuel
111. tags as each item is connected or installed WARNING THE AIRCRAFT FUEL TANKS AND LINES MUST BE PURGED TO REMOVE ALL CONTAMINATION PRIOR TO INSTALLATION OF THE MAIN FUEL INLET LINE TO THE FUEL PUMP FAILURE TO COMPLY CAN CAUSE ERRATIC FUEL SYSTEM OPERATION AND DAMAGE TO ITS COMPONENTS WARNING DO NOT INSTALL THE IGNITION HARNESS B NUTS ON THE SPARK PLUGS UNTIL THE PROPELLER INSTALLATION IS COMPLETED FAILURE TO COMPLY COULD RESULT IN BODILY INJURY WHEN THE Installation amp Operation Manual O 360 and 10 360 Series Engines WZ i anlage Engine Install the approved propeller in accordance with the manufacturer s instructions Outline Drawings for the installation design are located in the Model Specification Data These illustrations are provided by engine series and therefore include reference dimensions only Full size detailed installation drawings may be obtained from Superior Air Parts Engineering 4 INSTRUMENTATION CONNECTIONS Superior Vantage Engines are provided with accommodations for standard engine monitoring instrumentation Table 4 1 describes these instrument connections PROPELLER IS ROTATED DURING INSTALLATION Table 4 1 Instrumentation Connections Instrument Qty Connection O 10 3 8 24 UNF Thread with 1 0 deep hole to receive WD 4 AN4076 1 or equivalent thermocouple Fitting type Fig 1 2 Fig 1 6 H J Thermocouple recommended 5 8 18 UNF Thread with 2 7 16 deep hole to Oil Temper
112. te seal leakage and a negative pressure could increase the flowrate out of the crankcase and cause loss of engine oil Superior recommends installation of an air oil separator as part of a vacuum pump installation The oil drain may be connected into a cylinder head drain back tube or other location as approved by Superior Air Parts Chapter 3 Aircraft Engine Integration Considerations SUPERIZR Installation amp Operation Manual p A Engine EF O 360 and 10 360 Series Engines Vernatherm Oil Pump Valve Oil Filter i Gr To From Bypass Valve x a Vacuum Oil Cooler Oil Cooler Pum Oil Pressure Oil Sump Vacuum Pump aad Heli a Suction Screen Splash Oil To m Tach Drive Cyl 4 Piston Drain To Sump Cooling Nozzle If installed Idler Gears No 3 Main Fi Bearing Left Crankcase Right Crankcase Oil Galley Oil Galley Splash Oil Cyl 2 3 4 d To Pistons Crankpins v Cams Et ams EIC Cyl 2 amp 3 Piston Cooling Nozzle If installed Lifters Lifters Left Side lt N Right Side P E 7 No 2 Main NI N Bearing 3 y Push Push A Rod Rod Push ael Tubes Camshaft Camshaft Tubes Rods ods Journal No 2 Journal No 3 1 Rocker Rocker Arm Thrust Arm Splash Oil Splash Oil i Bushings To Rocker Camshaft race To Rocker SE Arms Valves Journal No 1 Arms Valves Etc Etc No 1 Main Bearing Splash Oil d To Pistons cym Cams Etc Cyl 1 Crankpin Cyl 1 Pisto
113. tion regarding airframe inspections WARNING FUEL IS TOXIC AND FLAMMABLE DO NOT BREATHE VAPORS USE IN A WELL VENTILATED AREA FREE FROM SPARKS FLAME OR HOT SURFACES PUT ON SPLASH GOGGLES SOLVENT RESISTANT GLOVES AND OTHER PROTECTIVE GEAR IN CASE OF EYE CONTACT FLUSH WITH WATER FOR 15 MINUTES AND SEEK MEDICAL ATTENTION IN CASE OF SKIN CONTACT WASH WITH SOAP AND WATER March 2004 Superior Air Parts Inc Installation amp Operation Manual O 360 and 10 360 Series Engines N27 i antage Engine 5 DAILY PRE FLIGHT INSPECTION A The Daily Pre Flight Inspection Check This is a check of the aircraft s general condition prior to the first flight of the day A proper pre flight inspection is essential for flight safety B Perform Inspection Checks as follows 1 Be sure all switches are in the Off position 2 Be sure magneto ground wires are connected 3 Visually inspect the engine and propeller for any damage oil or fuel leaks security and proper servicing 4 Check oil level in sump add oil as necessary 5 See that fuel tanks contain fuel of the proper type and quantity see Chapter 3 section 3E 6 Check fuel and oil line connections Repair any leaks before aircraft is flown NOTE Record any minor discrepancies for further inspection at the next 50 hour Inspection 7 Drain a guantity of fuel from all sumps and strainers into a clean container If water or foreign matte
114. tions traveled from one exhaust pipe and back up another excessive pressure could be present as the second cylinder s exhaust valve opened and cause a disruption to the exhaust gas exit High back pressure whether caused from basic system flow restrictions or pressure waves of adjacent cylinders can have significant effects on volumetric efficiency and thereby on power output and fuel efficiency A third exhaust system style is commonly referred to as a crossover design This style connects the exhaust pipes of two cylinders in such a manner as to enhance performance In an ideal crossover system as the pressure wave from one cylinder passes the connection point of the two exhaust pipes a slight suction is created in the exhaust pipe of the second cylinder When properly tuned this suction is caused as the exhaust valve of the second cylinder opens and aids in the emptying of the second cylinder The pressure wave of the second cylinder then creates a slight suction in the exhaust pipe of the first cylinder aiding in its emptying This behavior improves the breathing of the cylinders and can have volumetric efficiency power and fuel efficiency benefits For Superior Vantage Engines with 4 cylinders crossover exhaust systems should couple cylinder 1 with cylinder 2 and cylinder 3 with cylinder 4 Crossover exhaust systems are typically less space efficient and a little heavier than other styles but have the unique benefit of
115. ttachment of the engine to the shipping fixture This hardware is not suitable for the structural requirements of an engine installation and it is important to verify that it is not used in that regard A lifting eye bracket is installed on the backbone of each engine crankcase for the purposes of hoisting the engine Note This is the only means by which the engine should be lifted Lifting the engine by any other means may result in damage to the engine and is not covered by warranty The following includes a discussion of general engine installation practices This discussion should be used IN ADDITION TO the applicable requirements of the FARs 2 PREPARING ENGINE FOR SERVICE If the engine has been preserved for extended storage remove the shipping plugs installed in the lower spark plug holes and turn the crankshaft through at least twice in order to remove the cylinder preservation oil from the cylinders Remove the shipping plugs installed in the upper spark plug holes and inspect the cylinder bores for rust or contamination Contact Superior if any abnormal condition is noted March 2004 Superior Air Parts Inc Engines that have been subjected to a cold environment for long periods of time should be placed into at least 70 F atmosphere for 24 hours or more before attempting to drain the preservative oil Alternatively the cylinders may be heated with heating lamps before attempting to drain the engine Remov
116. unt of supplementary cooling required for these engine accessories is installation specific and must be determined by testing Temperature limits for these accessories are specified in the Model Specification Data Chapter 3 Aircraft Engine Integration Considerations SUPERIZR P BA ETS 5 EXHAUST SYSTEM The engine exhaust system s primary role is to transfer engine exhaust gasses from the cylinder heads overboard in a safe and efficient manner Exhaust systems serve to reduce engine noise provide heat sources for carburetor and cabin heaters and even act to enhance engine performance in terms of both power and fuel efficiency Improperly designed exhaust systems can create health risks to aircraft occupants and can be detrimental to engine performance A Health and Safety Issues Carbon monoxide is a colorless odorless gas that is potentially lethal and a basic by product of internal combustion engines The primary role of exhaust systems to safely conduct this gas from the combustion chamber away from persons on board the aircraft cannot be overstated Exhaust systems must be airtight with no potential for carbon monoxide leaks and must exit outside the aircraft in a location where gases will not be reintroduced to the airframe Due to the extreme temperature of exhaust system components up to 1600 F care must also be taken to isolate combustible materials This includes flammable liquids such as fuel oil and hy
117. with a plug located in each end of the pin The piston is a 3 ring type with 2 compression rings and 1 oil control ring Cooling System Superior Vantage Engines are designed to be air cooled Baffles are provided to build up air pressure and force the air between the cylinder fins The air is exhausted to the atmosphere through the rear of the cowling Induction System The distribution of the air to each cylinder is through the center zone of the induction system This is integral with the oil sump Fuel Systems Carbureted Superior Air Parts O 360 engines are equipped with a float type carburetor The MA 4 5 carburetors are of the single barrel float type equipped with a manual mixture control and an idle cut off Fuel Injected 10 360 series engines are equipped with a direct cylinder injected RSA 5 fuel injector The fuel injection system schedules fuel flow in proportion to airflow Fuel vaporization takes place at the intake ports The RSA fuel injection system is based on the principle of measuring airflow and using the air pressure in a stem type regulator converting the air pressure into a fuel pressure The fuel pressure fuel pressure differential when applied across the fuel metering section jetting system makes fuel flow proportional to airflow Lubrication System The full pressure wet sump lubrication system is supplied by a gear type pump It is contained within the accessory housing Priming System
118. y inspection intervals 3 OTHER MANDATORY INTERVALS OR PROCEDURES Subject to additional information contained in F A A Approved Mandatory Service Bulletins issued after the date of certification the O 360 and 10 360 engine series do not have any inspection related or replacement time related procedures required for type certification March 2004 Superior Air Parts Inc 4 DISTRIBUTION OF CHANGES TO AIRWORTHINESS Changes to this Airworthiness Limitations Chapter constitute changes to the type design of the O 360 and 10 360 engine series and require F A A approval pursuant to Federal Aviation Regulations Such changes will be published in F A A Approved Mandatory Service Bulletins Superior Vantage Engine Service Bulletins may be obtained by writing to Superior Air Parts 621 South Royal Lane Suite 100 Coppell Texas 75019 or call 972 829 4600 or on the web at www superior air parts com Chapter 2 Airworthiness Limitations A IS Installation amp Operation Manual O 360 and IO 360 Series Engines WZ i anlage Engine CHAPTER 3 Aircraft Engine Integration Considerations 1 GENERAL The following sections in this chapter include a discussion of design practices to be considered during the integration of a Superior Vantage engine with an airframe and propeller These discussions should be used IN ADDITION TO the applicable requirements of the FARs Superior requires that proper functioning of th

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