# Continental IO-240-A - Type: Engine model (FAA registry) - Registry code: 17166 - Manufacturer (registry): CONT MOTOR - Model: IO-240-A - Engine type: Reciprocating - Power: 125 hp - Data sheet: [TCDS E7SO](https://openairdocs.org/tcds/E7SO) (OpenAirDocs) - Holder: Continental Aerospace Technologies, Inc. - Installed in: 1 registered aircraft - Page: https://openairdocs.org/engine/continental-io-240-a Model codes come from the FAA registry's reference file. ## ADs that may apply (OpenAirDocs) Matched to this engine model by model name and maker. Each AD's applicability may narrow it by serial number, part number or equipment. - [AD 2012-03-06](https://openairdocs.org/ad/2012-03-06): Fuel servo diaphragm · Continental Motors 6-260-A, 6-285-A, 6-285-B and 482 more. Effective Feb 24, 2012 - [AD 2010-11-04](https://openairdocs.org/ad/2010-11-04): Hydraulic lifters · Continental Motors FSO-470-A, GIO-470-A, GTSIO-520-C and 190 more. Effective Jun 16, 2010 Historical (superseded or no longer in force): - [AD 2009-24-51](https://openairdocs.org/ad/2009-24-51) (historical): Hydraulic lifters · Teledyne Continental Motors FSO-470-A, GIO-470-A, GTSIO-520-C and 156 more ## Information bulletins (advisory) (5) - [SAIB NE-16-13](https://openairdocs.org/saib/NE-16-13): Powerplant - Prohibited use of sealant. Issued Mar 8, 2016 - [SAIB NE-13-15](https://openairdocs.org/saib/NE-13-15): Engine Controls: Continental Motors, Inc. (CMI) Throttle and Mixture Control Levers. Issued Feb 8, 2013 - [SAIB NE-13-04](https://openairdocs.org/saib/NE-13-04): Continental Motors, Inc. (CMI) Connecting Rod Piston Pin Bushing Inspection. Issued Oct 31, 2012 - [SAIB NE-10-09](https://openairdocs.org/saib/NE-10-09): Reciprocating Engine Power Section: Hydraulic Valve Lifters. Issued Nov 20, 2009 - [SAIB CE-98-21R1](https://openairdocs.org/saib/CE-98-21R1): . Issued Jun 10, 1998 ## Registered aircraft (1) - [N2276D](https://openairdocs.org/aircraft/N2276D): built 1996, S/N 010 ## NTSB investigations None matched to aircraft with this engine model. ## FAA accident and incident reports None matched to aircraft with this engine model. ## Service difficulty reports (29) As reported by operators and repair stations, by the model named in the report. - [SDR CA150110001](https://openairdocs.org/sdr/CA150110001), Jan 9, 2015: GASKET. FAILED. (CAN) DURING FUEL SENDER REPLACEMENT IT WAS NOTED THAT THE SENDER GASKET WAS SWELLED AND CRACKING. GASKET WAS REPLACED WITH SENDER. SENDER HAD BEEN REPLACED 534 - [SDR 2014FA0000086](https://openairdocs.org/sdr/2014FA0000086), Feb 19, 2014: PUMP. MALFUNCTIONED. WHEN PULLING BACK ON FUEL/AIR MIXTURE CONTROL, ENGINE LEANS OUT MUCH QUICKER THAN NORMAL CAUSING ENGINE TO LOSE POWER ABRUPTLY AND STOP. - [SDR CA120802015](https://openairdocs.org/sdr/CA120802015), Jul 27, 2012: COTTER PIN. BROKEN. (CAN) DURING ROUTINE INSPECTION WHILE CHANGING THE ENGINE OIL, WE FOUND A SMALL PIECE OF COTTER PIN ON THE OIL DRAIN PLUG MAGNET. BOTH MAGNETO WERE REMOVED AND - [SDR 2010FA0000536](https://openairdocs.org/sdr/2010FA0000536), May 27, 2010: TUBE. WORN. PILOT RUDDER PEDAL "S" TUBE WORN THROUGH. - [SDR 2009FA0000940](https://openairdocs.org/sdr/2009FA0000940), Oct 25, 2009: COUPLING. FAILED. ALTERNATOR DRIVE COUPLING FAILED IN FLIGHT CAUSING LOSS OF ALL ELECTRICAL CHARGING CAPABILITY. FLIGHT CONTINUED TO HOME BASE WITHOUT INCIDENT. THIS IS THE SECON - [SDR 2009FA0000939](https://openairdocs.org/sdr/2009FA0000939), Nov 15, 2006: COUPLING. FAILED. ALTERNATOR DRIVE COUPLING (ONE PIECE UNIT) FAILED IN FLIGHT. LOSS OF ALL ELECTRICAL CHARGING CAPABILITY. OCCURRED DURING NIGHT FLIGHT. UNSCHEDULED LANDING MADE. - [SDR 2006FA0000019](https://openairdocs.org/sdr/2006FA0000019), Jan 9, 2006: ROLL PIN. MISSING. ROLL PIN LOCKING THE NOSE STRUT ELASTOMERIC SPRING PLATE (PN 20-3220-05-02) TO THE SHOCK ABSORBER ROD (PN 20-3220-05-01) HAD WORKED OUT UNLOCKING THE ASSY. - [SDR 2005FA0001646](https://openairdocs.org/sdr/2005FA0001646), Dec 20, 2005: ROLL PIN. LOOSE. ROLL PIN LOCKING THE NOSE STRUT ELECTROMETRIC SPRING PLATE (PN 20-3220-05-02) TO THE SHOCK ABSORBER ROD (PN 20-3220-05-01) HAD WORKED OUT UNLOCKING THE ASSY. - [SDR 2005FA0001647](https://openairdocs.org/sdr/2005FA0001647), Dec 20, 2005: ROLL PIN. LOOSE. ROLL PIN LOCKING THE NOSE STRUT ELECTROMETRIC SPRING PLATE (PN 20-3220-05-02) TO THE SHOCK ABSORBER ROD (PN 20-3220-05-01) HAD WORKED OUT UNLOCKING THE ASSY. - [SDR 2005FA0001532](https://openairdocs.org/sdr/2005FA0001532), Nov 10, 2005: LANDING GEAR. UNLOCKED. ROLL PIN LOCKING THE NOSE STRUT ELECTROMETRIC SPRING PLATE (PN 20-3220-05-02) TO THE SHOCK ABSORBER ROD (PN 20-3220-05-01) HAD WORKED OUT UNLOCKING THE ASSY. - [SDR 2005FA0001521](https://openairdocs.org/sdr/2005FA0001521), Nov 4, 2005: FUEL TANK. CRACKED. DURING OUTER MAINTENANCE FOUND FUEL TANK CRACKED IN NP SURFACE AT CENTERAL APT SPOT WELD FOR INTERNAL BAFFEL. INSTALLED NEW FUEL TANK TO CORRECT PROBLEM. (K) - [SDR 2005FA0001444](https://openairdocs.org/sdr/2005FA0001444), Oct 5, 2005: CANOPY. SEPARATED. GLASS SEPARATING FROM FRAME. (EA07200505548) (K) - [SDR 2005FA0001445](https://openairdocs.org/sdr/2005FA0001445), Oct 5, 2005: CANOPY. SEPARATED. CANOPY GLASS SEPARATING FROM FRAME. (EA07200505547) (K) - [SDR 2005FA0001291](https://openairdocs.org/sdr/2005FA0001291), Sep 2, 2005: CONTROL TUBE. CORRODED. THE IB RT FLAP AND SECTION OF THE FLAP CONTROL TUBE WERE EXAMINED. THE CONTROL TORQUE TUBE WELD CONTAINED SURFACE CORROSION AND A FATIGUE CRACK WAS NOTED. - [SDR 2005FA0001397](https://openairdocs.org/sdr/2005FA0001397), Nov 4, 2004: THROTTLE CABLE. FAILED. THROTTLE CABLE BROKEN INSIDE OF CABLE HOUSING 26 INCHES FROM CABLE END. NOTED THAT CABLE ASSEMBLY MAKES TIGHT RADIUS BEND BEHIND INSTRUMENT PANEL, JUST AFT OF F - [SDR 2004FA0000230](https://openairdocs.org/sdr/2004FA0000230), Feb 20, 2004: SLEEVE. LOOSE. THE SLEEVE ON THE RUDDER HINGE PIN CAME LOOSE FROM ITS LOCTITED POSITION ON THE PIN AND WORKED UP INTO THE CAVITY ABOVE THE BEARING ON THE FIN. RUDDER HAD CONSI - [SDR 2004FA0000255](https://openairdocs.org/sdr/2004FA0000255), Jan 5, 2004: STALL WARNING. FROZEN. WE HAVE FOUND THAT THE STALL WARNING SYSTEM ON THIS TYPE OF AIRCRAFT IS PRONE TO FREEZE UP. MOISTURE IS INTRODUCED TO THE SYSTEM THROUGH THE SENSORY HOLE IN THE - [SDR AUS20030522](https://openairdocs.org/sdr/AUS20030522), May 12, 2003: BRACKET. CRACKED. (AUS) FLAP HINGE SUPPORT BRACKETS (PN 5731001-05 AND PN 5731001-02) CRACKED. RT INNER BRACKET FAILED AND LT INNER BRACKET CRACKED. - [SDR AUS20030126](https://openairdocs.org/sdr/AUS20030126), Jan 15, 2003: BOLT. SHEARED. (AUS) BOTTOM RT ENGINE MOUNT BOLT SHEARED. - [SDR 2002FA0001239](https://openairdocs.org/sdr/2002FA0001239), Sep 13, 2002: HINGE. CRACKED. DURING 100 HOUR INSPECTION MECHANIC FOUND CRACK ON LOWER RIGHT CORNER OF LOWER RUDDER HINGE SUPPORT TOWER NEXT TO THE WELD LINE. PART WAS REPLACED WITH NEW PART - [SDR 2002FA0000269](https://openairdocs.org/sdr/2002FA0000269), Feb 16, 2002: VALVE SPRING. FAILED. DURING ANNUAL INSPECTION, PERFORMED A COMPRESSION CHECK ON ALL ENGINE CYLINDERS. TWO CYLINDERS FAILED THE CHECK LEAKING BY THE VALVES. REMOVED CYLINDERS, DISASS - [SDR AUS20020086](https://openairdocs.org/sdr/AUS20020086), Jan 30, 2002: GEAR. WORN. (AUS) LH AND RH MAGNETO GEARS WORN. - [SDR AU990814](https://openairdocs.org/sdr/AU990814), Aug 17, 1999: EXHAUST PIPE. CRACKED. (AUS) ENGINE EXHAUST PIPE CRACKED IN THE AREA BELOW THE MOUNT FLANGE ATTACHMENT WELD. THE CRACK HAD PROGRESSED FOR APPROXIMATELY HALF OF THE PIPE CIRCUMFERENCE. - [SDR AU990698](https://openairdocs.org/sdr/AU990698), Jul 14, 1999: MUFFLER. CRACKED. (AUS) EXHAUST MUFFLER CRACKED IN THREE PLACES FROM SHROUD SUPPORT WELDS. CRACK LENGTHS ALL LESS THAN 12.7 MM (0.5 INCH). - [SDR AU990357](https://openairdocs.org/sdr/AU990357), Apr 19, 1999: EXHAUST PIPE. CRACKED. (AUS) NR 2 CYLINDER EXHAUST PIPE CRACKED AROUND THE CIRCUMFERENCE IN THE AREA JUST BELOW THE MOUNTING FLANGE. - [SDR AU990049](https://openairdocs.org/sdr/AU990049), Jan 25, 1999: EXHAUST PIPE. CRACKED. (AUS) NR 2 CYLINDER EXHAUST PIPE TO CYLINDER MOUNTING FLANGE CRACKED APPROXIMATELY 50.8 MM (2 INCHES) AROUND CIRCUMFERENCE OF WELD. FOUND DURING INSPECTION IAW - [SDR AU990047](https://openairdocs.org/sdr/AU990047), Jan 16, 1999: EXHAUST PIPE. CRACKED. (AUS) NR 2 AND NR 3 CYLINDER EXHAUST PIPE TO CYLINDER MOUNTING FLANGES CRACKED AROUND THE CIRCUMFERENCE OF THE WELD. CRACK LENGTH APPROXIMATELY 50.8 MM (2.0 INC - [SDR AU971353](https://openairdocs.org/sdr/AU971353), Oct 8, 1997: GEAR. DAMAGED. (AUS) ENGINE ACCESSORY DRIVE GEARS HAD DAMAGED AND BROKEN TEETH. - [SDR AU970730](https://openairdocs.org/sdr/AU970730), Jun 27, 1997: SEAL. LOOSE. (AUS) VACUUM PUMP DRIVE SHAFT SEAL LOOSE - FOUND WHEN PAD BLANKING PLATE REMOVED TO RECTIFY OIL LEAK - NO VACUUM PUMP FITTED TO THIS AIRCRAFT ## STCs that may be installed (OpenAirDocs) (5) Approved for this engine model: the STC's model list names it on its data sheet, or a series that includes it. In force first, then newest. The registry doesn't record which STCs an aircraft has. - [STC SE00145WI](https://openairdocs.org/stc/SE00145WI): Installation of B&C Specialty Products Model BC 320-( ) Engine Starter. B & C Specialty Products Inc - [STC SE03232CH](https://openairdocs.org/stc/SE03232CH): Installation of Engine Preheat Kit p/n TA2925-1 for 115 volt application. Hartzell Propeller Inc - [STC SE04577CH](https://openairdocs.org/stc/SE04577CH): Install an electronic engine ignition system. Electroair Acquisition Corp - [STC SE01966WI](https://openairdocs.org/stc/SE01966WI): Use of GAMI G100UL High Octane Unleaded Avgas in spark ignition piston aircraft engines. General Aviation Modifications Inc - [STC SE09513SC](https://openairdocs.org/stc/SE09513SC): Installation and usage of Exxon 20W50 Multigrade aircraft engine oil conforming to Exxon Oil Formulation WS-3013. Exxon Company USA --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.