# Service difficulty reports: Continental IO-520-A A list on [Continental IO-520-A](https://openairdocs.org/engine/continental-io-520-a.md). Newest first. General aviation reporting is voluntary. Page 1 of 2 · 73 reports - [SDR S1ZA2019091300000](https://openairdocs.org/sdr/S1ZA2019091300000.md): Engine · failed · Sep 13, 2019 · N5152U · Cessna 206CESSNA · Engine (Reciprocating) > ENGINE FAILURE OVER OLD GROWTH FOREST. THE ENGINE HAD A LOUD BANG AND STARTED RUNNING VERY ROUGH ACCORDING TO PILOT. THE ENGINE SHOOK JUST AS BADLY WHILE OFF AND WINDMILLING AS IT DID WHEN THE ENGINE WAS RUNNING. PILOT LANDED AIRCRAFT IN A SWAMP WITH HEAVY - [SDR CA140516003](https://openairdocs.org/sdr/CA140516003.md): Cylinder · damaged · May 13, 2014 · Cessna 210G · Reciprocating Engine Cylinder Section > (CAN) CYLINDER NR 1 REMOVED DUE TO LOW COMPRESSION. PRIMARY LOSS OF COMPRESSION OBSERVED FROM CRANKCASE BREATHER, RINGS. CYLINDER REMOVED TO CORRECT CONDITION. IT WAS OBSERVED THAT THE NICKEL/CARBIDE FINISH HAS DELAMINATED FROM CYLINDER WALL. LOSS OF MATERIA - [SDR 2013FA0000499](https://openairdocs.org/sdr/2013FA0000499.md): Bearing · failed · Aug 15, 2013 · N982SF · Cessna P206E · Magneto/Distributor > PILOT REPORTED AN INOPERATIVE MAGNETO ON PREFLIGHT RUN UP. WHEN THE MAGNETO WAS REMOVED IT WAS NOTICED THAT THE ENDS OF THE PN 531178, DRIVE COUPLING RETAINER WERE MISSING, AND APPARENTLY WERE INGESTED DOWN INTO THE ENGINE ACCESSORY SECTION. THE MAGNETO WAS - [SDR 2013FA0000299](https://openairdocs.org/sdr/2013FA0000299.md): Saddle · cracked · May 21, 2013 · N4963U · Cessna 210E · Main Landing Gear > THE LT AND RT MAIN GEAR SADDLES WERE REPLACED 3-14-1977 AT TACH 1448.0 IAW AD76-14-07R2 AND SE75-26 THEY WERE DUE FOR A DY PENETRANT CHECK 1300 HRS LATER. THE DYE PENETRENT CHECK WAS DONE 42HRS EARLY TO CONINCIDE WITH OTHER MX. BOTH SADDLES WERE DISCOVERED T - [SDR 2013FA0000300](https://openairdocs.org/sdr/2013FA0000300.md): Saddle · cracked · May 21, 2013 · N4963U · Cessna 210E · Main Landing Gear > THE LT AND RT MAIN GEAR SADDLES WERE REPLACED 3-14-1977 AT TACH 1448.0. IAW AD76-14-07R2 AND SE75-26 THEY WERE DUE FOR A DY PENETRANT CHECK 1300 HRS LATER. THE DYE PENETRENT CHECK WAS DONE 42HRS EARLY TO CONINCIDE WITH OTHER MAINTENANCE. BOTH SADDLES WERE D - [SDR RTEA2013F00000](https://openairdocs.org/sdr/RTEA2013F00000.md): Distributor Gear · dislodged · Apr 1, 2013 · N4879F · Cessna U206A · Magneto/Distributor > ENGINE RAN ROUGH WHEN ON AFFECTED MAGNETO ONLY. DURING RUNUP FOR ROUTINE SCHEDULED INSPECTION. ON DISASSEMBLY OF MAGNETO, DISCOVERED THE DISTRIBUTOR FINGER HAD DISLODGE FROM THE DISTRIBUTOR GEAR, CAUSING ERRATIC TIMING. HAVE SEEN THESE FINGERS COME SLIGHTL - [SDR 2011FA0000306](https://openairdocs.org/sdr/2011FA0000306.md): Hub · cracked · May 6, 2011 · N389Z · Beech M35 · Propeller Hub Section > THE PROPELLER WAS INSPECTED FOR COMPLETE O/H AND THE HUB WAS FOUND TO HAVE A CRACKED BLADE RETENTION THREADS. THIS MODEL OF PROPELLER HAS A HISTORY OF CRACKING AND THE MFG HAS ADDED APROVISION TO RED DYE OIL, FILL THE PROPELLER FOR EARLY CRACK DETECTION, THE - [SDR 2011FA0000226](https://openairdocs.org/sdr/2011FA0000226.md): Bulkhead · cracked · Apr 4, 2011 · N982SF · Cessna P206E · Fuselage Main, Bulkhead > DURING INSP IAW AD72-07-09, DATED 10/17/1974, AND SL SE72-3, THE AFT BULKHEAD WAS FOUND CRACKED IN BOTH RUDDER CABLE CUTOUTS. UPON REMOVAL OF AFT BULKHEAD THE LT AND RT STABILIZER ATTACH BRACKETS, PN 0712629-3 AND PN 0712629-4 WERE ALSO FOUND CRACKED. - [SDR 2010FA0001240](https://openairdocs.org/sdr/2010FA0001240.md): Wire Harness · faulty · Dec 8, 2010 · N4879F · Cessna U206A · Ignition System Wiring > ENGINE MISFIRING AT ALL POWER SETTINGS. DIAGNOSED FAULT TO BE THE IGNITION HARNESS LEADS. UTILIZING AN EASTERN TECHNOLOGY IGNITION HARNESS TESTER. IT WAS DETERMINED ALL THE BOTTOM LEADS WERE EITHER INTERMITTENT OR NONFUNCTIONAL FOR BOTH MAGNETOS. INSTALLIN - [SDR RTE2010F00001](https://openairdocs.org/sdr/RTE2010F00001.md): Contact Breaker · inoperative · Sep 1, 2010 · N4879F · Cessna U206A · Magneto/Distributor > IT IS APPARENT THAT MFG MAGNETOS HAVE HAD THE CONTACT BREAKER ASSY REPLACED IAW SB2-06A, DATED 7/1/06 ARE EXPERIENCING RAPID INTERNAL TIMING CHANGES. THE CONDITION NOTED ON NUMEROUS ACFT EQUIPPED WITH 4300 AND 6300 SERIES MAGNETOS IS ALWAYS A TIMING ADVANCE O - [SDR AG2R91788.1](https://openairdocs.org/sdr/AG2R91788.1.md): Cylinder Head · cracked · Aug 21, 2009 · Reciprocating Engine Cylinder Section > EXHAUST SEAT CRACK TOO SEVERE FOR REPAIR. ACFT MFG, MODEL, SN, TOTAL TIME AND CYLCES ARE UNKNOWN. - [SDR 2006FA0000448](https://openairdocs.org/sdr/2006FA0000448.md): Fcu · worn · Apr 14, 2006 · Cessna 210E · Fuel Control/Reciprocating Engines > FOUND SHAFT AND LINKAGE EXCESSIVELY WORN. HAD COMPLETE ASSEMBLY OVERHAULED. (K) - [SDR XGN2005F00010](https://openairdocs.org/sdr/XGN2005F00010.md): Cylinder · cracked · Oct 11, 2005 · N1194A · Beech 36BEECH · Reciprocating Engine Cylinder Section > FOUND CRACK AT THE 100 HR INSPECTION. ON GOING PROBLEM WITH THE ECI CYLINDERS. (K) - [SDR 2005FA0001198](https://openairdocs.org/sdr/2005FA0001198.md): Wedge · broken · Jul 9, 2005 · N4933U · Cessna 210E · Power Lever > CABLE BROKE AT THE S3 WEDGE WHERE THE BARREL END CONNECTS TO THE INTERNAL CABLE. THIS AREA IS NOT VISIBLE AS THERE IS AN INTERNAL SLEEVE THAT COVERS THE CABLE IN THIS AREA. ( CE07200516270) (K) - [SDR 2005FA0001012](https://openairdocs.org/sdr/2005FA0001012.md): Cylinder Head · cracked · Jun 17, 2005 · N210AW · Cessna 210D · Reciprocating Engine Cylinder Section > ENGINE WITH 450.0 TIS AND CYLINDER NR 2 WITH THE SAME TIS, BUT 31.0 HOURS SINCE REMOVAL/REPAIR/REINSTALLATION. DURING CRUISE FLIGHT, ENG BECAME VERY ROUGH WITH LOSS OF POWER. NORMAL LANDING WAS MADE. UPON INSP OF ENG, FOUND NR 2 CYL (COLD). PERFORMED COMPR - [SDR 2005FA0000168](https://openairdocs.org/sdr/2005FA0000168.md): Stud · failed · Oct 26, 2004 · N2625X · Cessna P206 · Reciprocating Engine Power Section > (2) EA DECK STUDS ON NR 1 CYLINDER FAILED. (K) - [SDR AOC04005](https://openairdocs.org/sdr/AOC04005.md): Cylinder · chipped · Jul 28, 2004 · Cessna 206CESSNA · Reciprocating Engine Cylinder Section > UPON RECEIVING INSPECTION OF NEW ECI CYLINDERS, ONE CYLINDER WAS FOUND TO HAVE THE NICKEL PLATING CHIPPED (.7500 INCH LONG X.0312 INCH WIDE) AT THE BASE OF THE CYLINDER SKIRT. PACKAGING APPEARED TO BE ADEQUATE AND THE CYLINDER WAS NOT DROPPED. SUSPECT PROBLEM - [SDR 2004FA0000685](https://openairdocs.org/sdr/2004FA0000685.md): Cylinder Head · cracked · Jun 9, 2004 · Reciprocating Engine Cylinder Section > HOLE THROUGH HEAD OR EXHAUST SIDE, NR7707-14, NR 7707-5 CRACKED HEAD. EST 500 HOURS SINCE NEW. - [SDR 2004FA0000516](https://openairdocs.org/sdr/2004FA0000516.md): Arm · inoperative · May 19, 2004 · N4916U · Cessna 210E · Landing Gear Door Retract Section > NOSE GEAR ON THIS AC WOULD NOT EXTEND DURING NORMAL, SUBSEQUENT EMERG L/G EXTEND PROCEDURE. UPON JACKING AC, FREEING NOSE GEAR, IT WAS DISCOVERED NOSE L/G DOOR ACTUATION ARM AND ROLLER ASSY WAS POSITIONED ON AFT SIDE OF NOSE GEAR FORK. WHEN WEIGHT OF AC WAS - [SDR 031311](https://openairdocs.org/sdr/031311.md): Pump · wrong part · Nov 7, 2003 · N4879F · Cessna U206A · Vacuum Distribution System > DURING PRE-PURCHASE EVALUATION FOUND DRY VACUUM PUMP INSTALLED AT ENGINE OVERHAUL APPROX 90 HOURS AGO. ORIGINAL PUMP WAS WET TYPE. ALL PLUMBING FOR WET PUMP WAS UTILIZED WITH DRY PUMP INSTALLED WITH NON STANDARD FITTINGS. NO APPROVAL FOR INSTALLATION OF DRY PU - [SDR AUS20030419](https://openairdocs.org/sdr/AUS20030419.md): Control Cable · separated · Apr 11, 2003 · Cessna U206 · Power Lever > (AUS) THROTTLE CABLE OUTER GUIDE SEPARATED FROM SWAGED SWIVEL JOINT ALLOWING CABLE TO FAIL IN COMPRESSION. - [SDR AUS20030345](https://openairdocs.org/sdr/AUS20030345.md): Bearing · worn · Mar 7, 2003 · Cessna U206 · Reciprocating Engine Power Section > (AUS) CONNECTING ROD BIG END BEARING WORN EXCESSIVELY. - [SDR 2002FA0001399](https://openairdocs.org/sdr/2002FA0001399.md): Nut · loose · Dec 4, 2002 · N95PY · Cessna 210E · Reciprocating Engine Oil System > LARGE LOCKNUT ON OIL FILTER ADAPTER CAME LOOSE AND OIL WENT OVERBOARD AND THE ENGINE SEIZED. THE AIRCRAFT LANDED IN A FIELD. THE SAFETY WIRE WAS STILL ATTACHED. - [SDR AUS20021008](https://openairdocs.org/sdr/AUS20021008.md): Fitting · cracked · Aug 30, 2002 · Cessna U206B · Fuselage, Stabilizer Attach Fittings > (AUS) FORWARD FIN ATTACHMENT FITTING CRACKED IN AREA ADJACENT TO THE LH BOLT HOLE. FOUND DURING INSPECTION IAW AD/C206/7A4. - [SDR 2001FA0000578](https://openairdocs.org/sdr/2001FA0000578.md): Skin · damaged · Nov 15, 2001 · N210KE · Cessna 210D · Horizontal Stabilizer, Plate/Skin > DURING AN ANNUAL INSPECTION THE RIGHT INBOARD SKIN HAD EXCESSIVE OIL CANNING WHEN FLEXED. WHEN FAIRING, PN 12124265 AND 12124266 (RIGHT AND LEFT) WERE REMOVED, THE RIGHT UPPER SKIN SURFACE UNDER FAIRING WAS CHAFFED THROUGH 4 INCHES IN LENGTH THE LEFT SKIN IN - [SDR 2001FA0000579](https://openairdocs.org/sdr/2001FA0000579.md): Skin · damaged · Nov 15, 2001 · N210KE · Cessna 210D · Horizontal Stabilizer, Plate/Skin > DURING AN ANNUAL INSPECTION THE RIGHT INBOARD SKIN HAD EXCESSIVE OIL CANNING WHEN FLEXED. WHEN FAIRING, PN 12124265 AND PN 12124266 (RIGHT AND LEFT) WERE REMOVED, THE RIGHT UPPER SKIN SURFACE UNDER FAIRING WAS CHAFFED THROUGH 4 INCHES IN LENGTH THE LEFT SKIN - [SDR AUS20010516](https://openairdocs.org/sdr/AUS20010516.md): Spring · failed · Apr 12, 2001 · Cessna U206 · Engine Starter > (AUS) STARTER CLUTCH SPRING FAILED CAUSING DAMAGE TO THE CRANKSHAFT,CAMSHAFT GEAR AND ATTACHING HARDWARE. ROCKWELL HARDNESS TESTREVEALED INCONSISTANT HARDNESS. - [SDR CA001218021](https://openairdocs.org/sdr/CA001218021.md): Throttle Cable · failed · Nov 29, 2000 · Cessna 207A · Power Lever > (CAN) A/C WAS BEING PREPARED FOR THE DAYS FLYING WHEN THE PILOT NOTICED THE THROTTLE WAS STIFF. HEAT WAS APPLIED TO THE CABIN AS IT WAS -22 DEGREES OAT. THE CABLE GOT STIFFER AND FAILED. THE INTERNAL CABLE FAILED AT SWAGGED END BY THE THROTTLE HAND KNOB. THE - [SDR AU000847](https://openairdocs.org/sdr/AU000847.md): Angle · corroded · Sep 13, 2000 · Cessna U206B · Wing, Fuselage Attach Fittings > (AUS) LEFT AND RIGHT WING FORWARD ATTACHMENT FITTING ANGLES CONTAINED INTERGRANNULAR CORROSION. (X) - [SDR AU000813](https://openairdocs.org/sdr/AU000813.md): Bulkhead · cracked · Sep 12, 2000 · Cessna U206B · Fuselage Main, Bulkhead > (AUS) FORWARD DOORPOST BULKHEAD CRACKED ON LEFT AND RIGHT SIDES. (X) - [SDR AU000814](https://openairdocs.org/sdr/AU000814.md): Angle · corroded · Sep 12, 2000 · Cessna U206B · Wing Spar > (AUS) RIGHT WING LOWER SPAR CAP ANGLE CONTAINED INTERGRANNULAR CORROSION. (X) - [SDR AU000815](https://openairdocs.org/sdr/AU000815.md): Angle · corroded · Sep 12, 2000 · Cessna U206B · Wing Spar > (AUS) LEFT WING UPPER SPAR CAP ANGLE CONTAINED EXFOLIATION CORROSION. (X) - [SDR AU000674](https://openairdocs.org/sdr/AU000674.md): Impulse Coupling · faulty · Sep 1, 2000 · Cessna U206 · Magneto/Distributor > (AUS) MAGNETO IMPULSE COUPLINGS (2OFF) HAD LOOSE RIVETS IN THE FLYWEIGHT ASSEMBLIES. FOUND DURING INSPECTION IAW SLICK SB 1-86B. (X) - [SDR 20000908SH008](https://openairdocs.org/sdr/20000908SH008.md): Points · failed · Aug 15, 2000 · N527NR · Cessna U206 · Magneto/Distributor > DURING PRE-INSPECTION RUN-UP BY MECHANIC, FOUND UNUSUAL MAG DROP ON RIGHT MAGNETO REMOVED FOR TROUBLESHOOTING. FOUND THE POINT ASSY CONTACT LOOSE AND FALLING OUT OF SPRING ARM. REPLACED CONTACT ASSY. OPS CHECKED GOOD. THIS MAG HAD 184 HOURS SINCE A TCM OVE - [SDR 20000829SH012](https://openairdocs.org/sdr/20000829SH012.md): Throttle · broken · Aug 10, 2000 · N8630Z · Cessna P206C · Power Lever > PILOT STARTED TO REDUCE POWER IN ORDER TO LOSE ALTITUDE. AT THIS TIME, THE THROTTLE CABLE BROKE CAUSING A LOSS IN ENGINE POWER. PILOT MADE SAFE LANDING IN A REMOTE FIELD. UPON INSPECTION, MAINTENANCE PERSONNEL FOUND THROTTLE CABLE BROKEN JUST ABOVE THE CABL - [SDR CA000621021](https://openairdocs.org/sdr/CA000621021.md): Line · chafed · Jun 10, 2000 · Cessna 207A · Landing Gear Brake System > (CAN) DURING TAXI, THE PILOT NOTICED THE RT BRAKE HAD LESS PRESSURE THAN THE LT. AIRCRAFT RETURNED TO BLOCKS,. INVESTIGATION REVEALED THAT THE RT BRAKE LINE HAD BEEN CHAFED BY A FAIRING SCREW AND WAS LEAKING. BRAKE LINE REPLACED, SHORTER SCREWS INSTALLED IN - [SDR 99ZZZX4251](https://openairdocs.org/sdr/99ZZZX4251.md): Cylinder · cracked · Oct 27, 1999 · N210DT · Cessna 210G · Reciprocating Engine Cylinder Section > DURING INSPECTION, FOUND GREASE LIKE FLUID ON INDUCTION TUBES AND WHERE CYLINDER AND HEAD ATTACH. REMOVED AND SENT TO OVERHAUL SHOP. REPORTED CRACKED HEAD WILL COME OFF SOON. REMOVED AND REPLACED CYLINDER. SUBMITTER RECOMMENDED CHECKING THIS LOCATION AT CY - [SDR 20000621SH010](https://openairdocs.org/sdr/20000621SH010.md): Cooler · leaking · Oct 7, 1999 · Cessna 206CESSNA · Engine Oil Cooler > PART BEGAN LEAKING DURING NORMAL SERVICE DUE TO EPOXY FAILURE. EPOXY WAS USED OVER A CRACK IN THE OIL COOLER WHICH WORKED ITS WAY TO THE SURFACE OF THE HARDENED EPOXY. SUBMITTER RECOMMENDED ELIMINATING THE USE OF EPOXY IN OIL COOLERS. (X) - [SDR AU990731](https://openairdocs.org/sdr/AU990731.md): Frame · cracked · Jul 12, 1999 · Cessna P206B · Fuselage Main, Frame > (AUS) LEFT DOORPOST FRAME CRACKED. FUSELAGE SKIN RIVETS LOOSE IN AREA ADJACENT TO THE WING STRUT. - [SDR AU990732](https://openairdocs.org/sdr/AU990732.md): Bulkhead · cracked · Jul 12, 1999 · Cessna P206B · Fuselage Main, Bulkhead > (AUS) FUSELAGE AFT BULKHEAD LOCATED AT STN 209.0 CRACKED IN THE UPPER RT CORNER ADJACENT TO THE RT HORIZONTAL STABILIZER ATTACHMENT FITTING. - [SDR 99ZZZX4475](https://openairdocs.org/sdr/99ZZZX4475.md): Cylinder · failed · Jul 8, 1999 · N446G · Cessna 210D · Reciprocating Engine Cylinder Section > CYLINDER HEAD SEPARATED DURING FLIGHT. ACFT MADE PRECAUTIONARY LANDING. POST-INCIDENT INSP REVEALED NR 3 CYL HEAD SEPARATED BETWEEN ITS COOLING FINS. HEAD CRACKED, SEPARATED AT THREADS THAT SECURE CYL HEAD TO BARREL. EVIDENCE OF A 3 INCH CRACK NEAR EXH POR - [SDR AU990437](https://openairdocs.org/sdr/AU990437.md): Wire · broken · May 8, 1999 · Cessna 210H · DC Generator-Alternator > (AUS) ALTERNATOR GROUND LEAD HAD COME ADRIFT FROM ITS TERMINAL AT THE ALTERNATOR SOME TIME PREVIOUSLY AND HAD BEEN STOWED IN THE LOOM AND HAD NOT BEEN RETERMINATED. WITHOUT A GROUND, THE ALTERNATOR HAD BEEN GROUNDING THROUGH AN ALUMINIUM DUCT RESTING AGAINST - [SDR CA990521008](https://openairdocs.org/sdr/CA990521008.md): Piston Pin · corroded · May 3, 1999 · Cessna 206CESSNA · Reciprocating Engine Cylinder Section > (CAN) AIRCRAFT ENGINE WAS BROUGHT IN TO CARRY OUT CSB-99-3. WHEN PREPARING TO REINSTALL THE PISTON PINS, THE PINS WERE FOUND WITH SUBSTANTIAL CORROSION FOR THE TIME IN SERVICE. THE PARTS WILL BE SENT TO CONTINENTAL FOR EVALUATION. - [SDR AU990086](https://openairdocs.org/sdr/AU990086.md): Static System · contaminated · Jan 28, 1999 · Cessna U206B · Pitot/Static System > (AUS) STATIC SYSTEM CONTAMINATED WITH WATER. AIRCRAFT HAD BEEN PARKED IN THE OPEN DURING A RAIN STORM. - [SDR CA990129006](https://openairdocs.org/sdr/CA990129006.md): Hub · corroded · Nov 28, 1998 · Cessna P206A · Propeller Hub Section > (CAN) HEAVY EXTERNAL CORROSION ON THE PROPELLER HUB. - [SDR 98ZZZX4363](https://openairdocs.org/sdr/98ZZZX4363.md): Thru-Bolt · broken · Sep 29, 1998 · Reciprocating Engine Power Section > THRU-BOLT IN CRANKCASE FOUND BROKEN. - [SDR AU981431](https://openairdocs.org/sdr/AU981431.md): Hub · corroded · Aug 20, 1998 · Cessna U206C · Propeller Hub Section > (AUS) PROPELLER HUB SEVERELY CORRODED. - [SDR CA980623021](https://openairdocs.org/sdr/CA980623021.md): Cylinder · separated · Jun 15, 1998 · Cessna P206B · Reciprocating Engine Cylinder Section > (CAN) NR 5 CYLINDER WAS FOUND TO HAVE A CYLINDER SEPARATION. - [SDR CA980519002](https://openairdocs.org/sdr/CA980519002.md): Cover · cracked · May 4, 1998 · Cessna 206CESSNA · Reciprocating Engine Cylinder Section > (CAN) ENGINE OIL LEAK. INSPECTION FOUND NR 5 CYLINDER PUSH ROD COVER CRACKED AT BEAD. PUSH ROD COVER REPLACED. - [SDR CA970909007](https://openairdocs.org/sdr/CA970909007.md): Collar · broken · Aug 18, 1997 · Cessna P206B · Main Landing Gear Strut/Axle/Truck > (CAN) THE AIRCRAFT IS USED FOR TRANSPORTING SKY DIVERS AND IS SUBJECT TO LONG TAKEOFF RUNS AND CROSSWINDS. THIS CONDITION SUBJECTS THE LANDING GEAR STRUT TO HIGH STRESS LOADS WHICH CONTRIBUTED TO THE STRUT COLLAR FAILURE. Next page: https://openairdocs.org/engine/continental-io-520-a/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 = 'IO520A' ORDER BY difficulty_date DESC ``` This list as a web page: https://openairdocs.org/engine/continental-io-520-a/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.