# Service difficulty reports: Lycoming O-320-D2A A list on [Lycoming O-320-D2A](https://openairdocs.org/engine/lycoming-o-320-d2a.md). Newest first. General aviation reporting is voluntary. Page 1 of 2 · 67 reports - [SDR PO4R2016FA0000012](https://openairdocs.org/sdr/PO4R2016FA0000012.md): Cylinder Head · separated · Oct 15, 2015 · N507PC · Socata TB9CTAMPICO · Reciprocating Engine Cylinder Section > 2 SECONDS AFTER FULL POWER APPLICATION FOR TAKEOFF, A LOUD BANG WAS HEARD AND THE PILOT DETECTED SIGNIFICANT VIBRATION IMMEDIATELY. PILOT ABORTED TAKEOFF, LIMPED TO PARKING AND SHUTDOWN. VISUAL INSPECTION REVEALED NR 3 CYLINDER HEAD SEPARATION CONSISTENT WIT - [SDR CA121205007](https://openairdocs.org/sdr/CA121205007.md): Elt · no test · Dec 4, 2012 · Amtr · Emergency Locator Beacon > (CAN) WHILE TESTING THE ELT ON ITS ANNUAL CERTIFICATION IAW CAR 571, APPENDIX-G THE TRANSMITTING POWER OF THE UNIT STARTED. OK, BUT WITHIN THE 3 MINUTES THE TRANSMITTING POWER DROPPED WELL BELOW SPECIFICATIONS. ELT REMOVED FROM SERVICE. - [SDR 2011FA0000367](https://openairdocs.org/sdr/2011FA0000367.md): Attach Fitting · broken · Jun 14, 2011 · N349TW · Sympho SA160 · Fuselage, Landing Gear Attach Fittings > DURING REMOVAL OF INTERIOR UPHOLSTERY FOR OTHER MX, FOUND THAT THE LT FORWARD OTBD MLG ATTACHMENT BOLT FITTING THAT IS PART OF THE TUBE FUSELAGE WAS BROKEN COMPLETELY THROUGH ON BOTH SIDES. THIS FITTING IS A BUSHING THAT IS WELDED TO THE FUSELAGE TUBE THAT ATT - [SDR 2010FA0000460](https://openairdocs.org/sdr/2010FA0000460.md): Pressure Switch · binding · May 2, 2010 · N123MX · Amtr LANCAIR235 · Hydraulic System, Main > LANDING GEAR DID NOT EXTEND AND GEAR-UP LANDING WAS MADE. POST INCIDENT INSPECTION AND OPERATION CHECK DEMONSTRATED REPEATABLE FAILURE CONDITION. HYDRAULIC PRESURE SWITCH WAS SHOWN A SOURCE OF FAILURE. - [SDR CA100625004](https://openairdocs.org/sdr/CA100625004.md): Crankshaft · broken · Feb 28, 2010 · Reciprocating Engine Power Section > (CAN) ON FEB 28/10, DURING CRUISE FLIGHT ENGINE DEVELOPED A VIBRATION FOLLOWED WITHIN SECONDS BY A TOTAL SEIZURE. AIRCRAFT WAS LANDED WITHOUT INJURY TO PILOT OR PASSENGER BUT TOTAL LOSS OF AIRFRAME. DISASSEMBLY OF ENGINE REVEALED THE CRANKSHAFT HAD FRACTURED - [SDR 2008FA0000544](https://openairdocs.org/sdr/2008FA0000544.md): Alternator · failed · Jul 30, 2008 · Socata TB9 · AC Generator-Alternator > ALTERNATOR WILL FAIL ABOVE 2500 RPM, LOW VOLTAGE LIGHT COMES ON AND THE VOLTMETER INDICATES BATTERY VOLTAGE. OPS CHECK DURING GROUND RUNS ARE NORMAL MAX RPM DURING GROUND RUN 2400 RPM. ALTERNATOR APPEARS TO BE RPM SENSITIVE. POSSIBLE CAUSE: BRUSHES NOT RIDING - [SDR 2007FA0000784](https://openairdocs.org/sdr/2007FA0000784.md): Float · failed · Jul 8, 2007 · N12HE · Amtr RV9A · Fuel Control/Reciprocating Engines > THE ENGINE DIED ON FINAL TO AIRPORT, PUMPED THE THROTTLE, AND THE ENGINE STARTED RUNNING AGAIN, RETARDED THROTTLE, AND THE ENGINE DIED AGAIN. LANDED WITHOUT INCIDENT. COULD NOT GET THE ENGINE TO RESTART ON THE GROUND. ENGINE WAS STARTED THE NEXT DAY, THE FU - [SDR CA060426001](https://openairdocs.org/sdr/CA060426001.md): Mount · damaged · Apr 5, 2006 · Sympho SA160 · Engine Mount Section > (CAN) INSPECTION FOR ISSUANCE OF A C OF A AIRCRAFT TOTAL TIME: 2.8 HRS DURING THE INSPECITON OF THIS AIRCRAFT BY CIVIL AVIATION INSPECTOR, IT WAS NOTED THAT AN ENGINE CONTROL SUPPORT BRACKET WAS CONTACTING THE LOWER TUBE OF THE ENGINE MOUNT. NO DAMAGE TO THE - [SDR CA040823004](https://openairdocs.org/sdr/CA040823004.md): Carburetor · failed · Aug 20, 2004 · Slnsby T67C · Fuel Control/Reciprocating Engines > (CAN) DURING A LOCAL FLIGHT, PILOT REPORTED THAT THE THROTTLE WAS BINDING. AIRCRAFT LANDED SAFELY. THE MAINTENANCE INVESTIGATION INDICATED THAT THE CARBURETOR BUTTERFLY VALVE WAS EXTREMELY STIFF. THIS CARBURETOR WAS INSTALLED PRIOR TO THIS FLIGHT AND UPON RUN - [SDR CA031028004](https://openairdocs.org/sdr/CA031028004.md): Volt Regulator · failed · Oct 16, 2003 · Piper PA28160 · AC Regulator > (CAN) VOLTAGE REGULATOR FAILED AND ALSO CAUSED DAMAGE TO THE ALTERNATOR DIODES. THE ALTERNATOR DIODES WERE REPLACED, AND THE VOLTAGE REGULATOR REPLACED WITH A NEW VR200A UNIT. CHARGING SYSTEM TESTED OK. - [SDR CA030409014](https://openairdocs.org/sdr/CA030409014.md): Bellcrank · cracked · Apr 8, 2003 · Piper PA28160 · Aileron Control System > (CAN) FOUND BRACKET CRACKED FOR A LENGTH OF ABOUT 2 CENTIMETERS JUST BELOW FORWARD BOLT HOLE. DEFECT CAN ONLY BE SEEN WITH INSPECTION MIRROR FROM OUTBOARD INSPECTION HOLE. - [SDR AUS20021166](https://openairdocs.org/sdr/AUS20021166.md): Mount · cracked · Sep 13, 2002 · Avions R2160 · Engine Mount Section > (AUS) ENGINE MOUNT CRACKED IN SEVERAL AREAS. FURTHER INSPECTION FOUND BOTH LOWER ENGINE MOUNT BRACKETS LOCATED BEHIND THE FIREWALL ALSO CRACKED. LH AND RH TOP FUSELAGE SKINS REMOVED FOR INSPECTION ANDLH TOP MOUNT STRUCTURE FOUND CRACKED. LH RUDDER BAR ATTACHME - [SDR CA020917005](https://openairdocs.org/sdr/CA020917005.md): Rod End · broken · Sep 11, 2002 · Socata TB9 · Aileron Control System > (CAN) ON A SCHEDULED MAINTENANCE INSPECTION THE RT AILERON SWIVEL ROD END WAS FOUND STIFF. ON FURTHER INSPECTION THE BEARING RACE WAS FOUND BROKEN AND SOME OF THE BALL BEARINGS WERE MISSING. - [SDR AUS20020725](https://openairdocs.org/sdr/AUS20020725.md): Gear · stripped · Jul 16, 2002 · Fuji FA200160 · Magneto/Distributor > (AUS) RH MAGNETO DISTRIBUTOR GEAR HAD FIFTEEN TEETH STRIPPED. - [SDR AUS20020726](https://openairdocs.org/sdr/AUS20020726.md): Exhaust Valve · cracked · Jul 8, 2002 · Fuji FA200160 · Reciprocating Engine Cylinder Section > (AUS) NO3 CYLINDER EXHAUST VALVE HEAD CRACKED AND BURNT. - [SDR AUS20020475](https://openairdocs.org/sdr/AUS20020475.md): Spark Plug · fouled · May 19, 2002 · Avions R2160 · Spark Plug/Igniter > (AUS) NR 4 CYLINDER SPARK PLUGS FOULED. - [SDR AU010182](https://openairdocs.org/sdr/AU010182.md): Crankshaft · corroded · Mar 7, 2001 · Fuji FA200160 · Reciprocating Engine Power Section > (AUS) CRANKSHAFT INTERNAL BORE CORRODED. FOUND DURING INSPECTION IAWAD/LYC/102 AMDT2 PART 1 AND PART 2. - [SDR AU010184](https://openairdocs.org/sdr/AU010184.md): Pushrod · misinstalled · Mar 7, 2001 · Fuji FA200160 · Reciprocating Engine Power Section > (AUS) ENGINE PUSHRODS AND TAPPETS INCORRECTLY FITTED DURING ASSEMBLY FOLLOWING A BULK STRIP FOLLOWING A PROPELLER STRIKE. METAL CONTAMINATION OF ENGINE. - [SDR AU001323](https://openairdocs.org/sdr/AU001323.md): Fitting · cracked · Dec 13, 2000 · Avions R2160 · Wing, Attach Fittings > (AUS) RT WING REAR SPAR INBOARD ATTACHMENT BRACKET CRACKED. CRACKSAPPEAR TO INITIATE FROM THE ACCESS PANEL ON THE LOWER WING SKIN PANELS ARE NONSTANDARD ACCESS PANELS. - [SDR AU001324](https://openairdocs.org/sdr/AU001324.md): Fitting · cracked · Dec 13, 2000 · Avions R2160 · Wing, Attach Fittings > (AUS) LT WING REAR SPAR INBOARD ATTACHMENT BRACKET CRACKED. CRACKSAPPEAR TO INITIATE FROM THE ACCESS PANEL ON THE LOWER WING SKIN PANELS ARE NON STANDARD ACCESS PANELS. - [SDR CA000427020](https://openairdocs.org/sdr/CA000427020.md): Wire · corroded · Apr 17, 2000 · Slnsby T67C · Electrical Power System Wiring > (CAN) THE AUDIO SYS INVESTIGATED DUE TO REPEATED PROBLEMS RPTED BY PILOTS EVEN FOLLOWING MAINT CARRIED OUT. COMPLETE WIRING CHECKED FROM DASHBOARD TO HEADSET/PHONES & JACK. SHIELDING OF WIRE STRIPPED TO CHECK ITS CONDITION. IT OBSERVED THAT BARE WIRE STRAND - [SDR CA991210019](https://openairdocs.org/sdr/CA991210019.md): Engine · failed · Nov 24, 1999 · Avions R2160 · Engine (Reciprocating) > (CAN) ENGINE STOPPED AT ALT, ENG WOULD NOT RESTART. NO FAULTS WERE FOUND WITH ENG AT BENCH TEST AFTER INCIDENT. - [SDR AU990815](https://openairdocs.org/sdr/AU990815.md): Magneto · faulty · Aug 17, 1999 · Avions R2160 · Magneto/Distributor > (AUS) RIGHT MAGNETO FAULTY. - [SDR AU990737](https://openairdocs.org/sdr/AU990737.md): Magneto · faulty · Jul 30, 1999 · Avions R2160 · Magneto/Distributor > (AUS) MAGNETO FAULTY. ENGINE WAS JUST RECEIVED FROM OVERHAUL. - [SDR CA990223010](https://openairdocs.org/sdr/CA990223010.md): Tube · misinstalled · Feb 9, 1999 · Fuel Control/Reciprocating Engines > (CAN) DURING FLIGHT, THE PILOT NOTICED THROTTLE MOVEMENT WAS OBSTRUCTED. THE AIRCRAFT LANDED SAFELY. ON THE GROUND, THE THROTTLE OPERATION WAS NORMAL. ON REMOVAL OF THE AIR INTAKE, MAINTENANCE PERSONNEL FOUND THE PUMP DISCHARGE TUBE ASSEMBLY SITTING ON THE - [SDR AU990057](https://openairdocs.org/sdr/AU990057.md): Bolt · cracked · Jan 19, 1999 · Avions R2160 · Wing, Fuselage Attach Fittings > (AUS) WING SPAR BOLTS CRACKED UNDER THE BOLT HEAD. PART TC: 3,547. - [SDR AU990012](https://openairdocs.org/sdr/AU990012.md): Splice · cracked · Jan 13, 1999 · Avions R2160 · Wing Miscellaneous Structure > (AUS) LEFT WING AFT LOWER SPLICE PLATE CRACKED APPROXIMATELY 2 MM (0.079 INCH) IN LENGTH. ALSO, THE FORWARD RIGHT ANGLE DOUBLER WAS CRACKED IN THE LOWER BEND RADIUS FOR APPROXIMATELY 25 MM (0.984 INCH). FOUND IAW AD/ROBIN/8A2. PART TC: 5,707. - [SDR AU990017](https://openairdocs.org/sdr/AU990017.md): Bolt · cracked · Jan 13, 1999 · Avions R2160 · Wing, Fuselage Attach Fittings > (AUS) WHEN WING SPAR BOLTS WERE MAGNAFLUXED, (NOT A REQUIREMENT OF THIS AD), ALL 12 BOLTS WERE FOUND CRACKED UNDER HEAD. FOUND DURING COMPLIANCE WITH AD/ROBIN/8A2. PART TC: 5,707. - [SDR AU981274](https://openairdocs.org/sdr/AU981274.md): Skin · cracked · Sep 25, 1998 · Avions R2160 · Wing, Plate/Skin > (AUS) LEFT WING UPPER LEADING EDGE SKIN CRACKED IN AREA OF RIVET LINE ON THE MAIN SPAR. CRACK APPROXIMATELY 52.8 MM (2 INCHES) IN LENGTH LOCATED 209.55 MM (8.25 INCHES) OUTBOARD OF THE WING ROOT. CRACK APPROXIMATELY 19.05 MM (0.75 INCHES) LOCATED 514.35 MM ( - [SDR CA980810007](https://openairdocs.org/sdr/CA980810007.md): Tappet · failed · Jul 30, 1998 · Reciprocating Engine Power Section > (CAN) PILOT REPORTED A ROUGH RUNNING ENGINE. INITIAL INVESTIGATION FOUND THE HYDRAULIC TAPPET BODY AND SYSTEM HAD FAILED ON THE NR 4 CYLINDER INTAKE SIDE. THE ENGINE IS BEING SENT FOR TEARDOWN AND INVESTIGATION. FURTHER REPORT TO FOLLOW. - [SDR CA980602014](https://openairdocs.org/sdr/CA980602014.md): Crankshaft · pitted · May 23, 1998 · Piper PA28160 · Reciprocating Engine Power Section > (CAN) WHILE COMPLYING WITH AD 98-02-08 INSPECTION, PITS WERE FOUND IN THE CRANKSHAFT BORE. - [SDR 97ZZZX4497](https://openairdocs.org/sdr/97ZZZX4497.md): Spark Plug · broken · Oct 8, 1997 · N3420T · Cessna 177 · Spark Plug/Igniter > ENGINE RPM DROPPED TO APPROXIMATELY 2,000 RPM ON CLIMB-OUT. GROUND RUN-UP WAS NORMAL BEFORE AND AFTER FLIGHT AND DURING FIRST 200 FEET OF CLIMB OUT. INSPECTION OF INDUCTION, FUEL AND IGNITION SYSTEMS, REVEALED TWO AUBURN SR-87 AC PLUGS WITH BROKEN INSULATORS - [SDR 97ZZZX1224](https://openairdocs.org/sdr/97ZZZX1224.md): Crankshaft · cracked · Mar 18, 1997 · N508PC · Socata TB9 · Reciprocating Engine Power Section > THIS AIRCRAFT IS USED EXCLUSIVELY FOR FLIGHT TRAINING. ON PRE-FLIGHT, STUDENT AND INSTRUCTOR FOUND OIL ON THE COWLING. UPON INSPECTION, TWO CRACKS WERE FOUND ON THE CRANKSHAFT COVERGING AT THE RADIUS OF THE CRANKSHAFT AND CRANKSHAFT FLANGE. THIS ENGINE AND - [SDR AU970165](https://openairdocs.org/sdr/AU970165.md): Torque Link · broken · Feb 20, 1997 · Socata TB9 · Main Landing Gear Strut/Axle/Truck > (AUS) LH MAIN LANDING GEAR LOWER TORQUE LINK BROKEN AT INBOARD ATTACHMENT LUG - OUTBOARD LUG CONTAINS A HAIR LINE CRACK - RH MLG TORQUE LINK CONTAINS SOME PITTING IN THE ATTACHMENT LUG HOLES - [SDR AU970107](https://openairdocs.org/sdr/AU970107.md): Torque Link · broken · Feb 18, 1997 · Socata TB9 · Main Landing Gear Strut/Axle/Truck > (AUS) RH MAIN LANDING GEAR LOWER TORQUE LINK FAILED AT LOWER ATTACHMENT HOLES - [SDR CA961216013](https://openairdocs.org/sdr/CA961216013.md): Crankshaft · corroded · Dec 3, 1996 · Reciprocating Engine Power Section > (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN T - [SDR CA961216014](https://openairdocs.org/sdr/CA961216014.md): Crankshaft · corroded · Dec 3, 1996 · Reciprocating Engine Power Section > (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN T - [SDR CA961216015](https://openairdocs.org/sdr/CA961216015.md): Crankshaft · corroded · Dec 3, 1996 · Reciprocating Engine Power Section > (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN T - [SDR CA961216016](https://openairdocs.org/sdr/CA961216016.md): Crankshaft · corroded · Dec 3, 1996 · Reciprocating Engine Power Section > (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN T - [SDR CA961216017](https://openairdocs.org/sdr/CA961216017.md): Crankshaft · corroded · Dec 3, 1996 · Reciprocating Engine Power Section > (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN T - [SDR CA961216018](https://openairdocs.org/sdr/CA961216018.md): Crankshaft · corroded · Dec 3, 1996 · Reciprocating Engine Power Section > (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN T - [SDR CA961216019](https://openairdocs.org/sdr/CA961216019.md): Crankshaft · corroded · Dec 3, 1996 · Reciprocating Engine Power Section > (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN T - [SDR CA961216020](https://openairdocs.org/sdr/CA961216020.md): Crankshaft · corroded · Dec 3, 1996 · Reciprocating Engine Power Section > (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN T - [SDR CA961216021](https://openairdocs.org/sdr/CA961216021.md): Crankshaft · corroded · Dec 3, 1996 · Reciprocating Engine Power Section > (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN T - [SDR CA961216022](https://openairdocs.org/sdr/CA961216022.md): Crankshaft · corroded · Dec 3, 1996 · Reciprocating Engine Power Section > (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN T - [SDR CA961216023](https://openairdocs.org/sdr/CA961216023.md): Crankshaft · corroded · Dec 3, 1996 · Reciprocating Engine Power Section > (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN T - [SDR CA961216024](https://openairdocs.org/sdr/CA961216024.md): Crankshaft · corroded · Dec 3, 1996 · Reciprocating Engine Power Section > (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN T - [SDR CA961115002](https://openairdocs.org/sdr/CA961115002.md): Crankshaft · cracked · Oct 1, 1996 · Reciprocating Engine Power Section > (CAN) ENGINE RECEIVED FOR REPAIR FOR A CRANKSHAFT CRACKED AT THE MAIN BEARING JOURNAL EXTENDING FROM THE FRONT EXPANSION PLUG SEAT IN A SPIRAL (ANTI CLOCKWISE FROM THE FRONT) TO APPROXIMATELY HALF WAY BETWEEN THE FORWARD THRUST FACE AND THE CROSS FEED OIL HOLE - [SDR CA960916010](https://openairdocs.org/sdr/CA960916010.md): Crankshaft · cracked · Sep 3, 1996 · Reciprocating Engine Power Section > (CAN) PILOT REPORTED AN OIL LEAK IN THE PROP AREA AND AN OIL SMELL IN THE CABIN. INVESTIGATION REVEALED THAT THE CRANKSHAFT ASSEMBLY HAD A CRACK FROM THE PROP FLANGE GOING IN A SPIRAL AFT OF THE FLANGE ON THE CRANKSHAFT. THE CRACK WAS APPROXIMATELY 4.5" LONG A - [SDR CA960826065](https://openairdocs.org/sdr/CA960826065.md): Pushrod · broken · Aug 9, 1996 · Power Lever > (CAN) UPON PULLING THE THROTTLE BACK THE PUSHROD BROKE AT THE FORWARD THREADED END, WHERE IT ATTACHES TO THE CLEVIS ASSEMBLY. THE PILOT HAD ENOUGH TRAVEL TO PERFORM A SAFE LANDING. Next page: https://openairdocs.org/engine/lycoming-o-320-d2a/reports.md?page=2 ## The whole list in SQL Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS: ```sql SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet' WHERE engine_model_key = 'O320D2A' ORDER BY difficulty_date DESC ``` This list as a web page: https://openairdocs.org/engine/lycoming-o-320-d2a/reports --- 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.