# Service difficulty reports: Found FBA-2C A list on [Found FBA-2C](https://openairdocs.org/model/found-fba-2c.md). Newest first. General aviation reporting is voluntary. - [SDR CA080930002](https://openairdocs.org/sdr/CA080930002.md): Propeller · vibration · Sep 14, 2008 · Found FBA2C · Propeller Assembly > (CAN) PROPELLER REMOVED FOR EVALUATION DUE TO SMALL VIBRATION. NOT CONSIDERED SERIOUS. - [SDR CA061218002](https://openairdocs.org/sdr/CA061218002.md): Brush Block · worn · Nov 26, 2006 · Found FBA2C · Magneto/Distributor > (CAN) THE DISTRIBUTOR GEAR BRUSH WAS EXCESSIVELY WORN FOR HAVING 587.2 HOURS ON IT IN A COMPONENT DESIGNED WITH A 2000 HOUR TBD. BRUSH BUSHING AND MOUNT OF POOR QUALITY WHICH IF LEFT UNDETECTED WOULD RESULT IN FAILURE IN 2 OR 300 MORE HOURS IF BEARING AND BUSH - [SDR CA061129003](https://openairdocs.org/sdr/CA061129003.md): Master Link · defective · Nov 24, 2006 · Found FBA2C · Aileron Control System > (CAN) DURING FIGHT ID 2C3-30 THE MASTER LINK (N025) FELL OFF THE COPILOT’S AILERON CHAIN CAUSING A LOSS OF AILERON CONTROL FROM THE COPILOT’S SIDE. THE FLIGHT TEST ENGINEER WAS ABLE TO COLLECT ALL THE PIECES FROM THE MASTER LINK DURING THE FLIGHT HOLD AND THE - [SDR CA060920006](https://openairdocs.org/sdr/CA060920006.md): Bolt · broken · Sep 12, 2006 · Found FBA2C · Horizontal Stabilizer Structure > (CAN) UPON REMOVAL OF THE LT FINLET THE REAR ATTACH BOLT (P/N AN3-4A) BROKE. WHEN INSTALLING 4 NEW BOLTS IT WAS NOTICED THAT THE WASHER RODE UP ON THE RADIUS OF THE ATTACH BRACKET CAUSING STRESS ON THE BOLT. WHEN HOLE LOCATION WAS CHECKED AGAINST THE RT FINLET - [SDR 2006FA0000782](https://openairdocs.org/sdr/2006FA0000782.md): Fitting · undertorqued · Aug 2, 2006 · N753 · Found FBA2C · Fuel Storage > AS REPORTED FROM THE PILOT, THE MAINTENANCE VENDOR FOUND NUMEROUS FUEL FITTINGS WHICH CONNECT THE FUEL LINES TO THE HEADER TANKS TO BE SEEPING FUEL. APPROXIMATE TIME OF SERVICE 532 HOURS. PIPE THREADED FITTINGS HAD NO THREAD LUBE/SEALANT. THE VENDOR NOTED THAT - [SDR CA060424002](https://openairdocs.org/sdr/CA060424002.md): Fly Wire · broken · Apr 10, 2006 · Found FBA2C · Wheel/Ski/Float > THE AIRCRAFT IS EQUIPPED WITH AEROCET 3450 AMPHIBIAN FLOATS. AFTER A TWO-HOUR FLIGHT AND AT 3000 FT ALTITUDE ON APPROACH FOR LANDING, THE PILOT HEARD A LOUD NOISE. NO TURBULENCE WAS NOTED AT THE TIME AND AN UNEVENTFUL LANDING WAS COMPLETED. UPON GROUND INSP - [SDR CA051110003](https://openairdocs.org/sdr/CA051110003.md): Lug · failed · Nov 10, 2005 · Found FBA2C · Wheel/Ski/Float > (CAN) DURING WALK-AROUND, LT REAR FLOAT FLY-WIRE WAS FOUND LOOSE. FURTHER INSPECTION REVEALED THE LT, AFT FLY-WIRE ATTACH LUG HAD FAILED APPROX 1/4 INCH FROM THE REAR FUSELAGE ATTACH POINT. REMAINING 3 FLY-WIRE ATTACH LUGS INSPECTED, NO FAULT FOUND. BROKEN SEC - [SDR CA050920008](https://openairdocs.org/sdr/CA050920008.md): Cylinder Bore · damaged · Aug 9, 2005 · Found FBA2C · Reciprocating Engine Cylinder Section > (CAN) PILOT NOTICED INCREASED CHT IN FLIGHT UTILIZING GEM (GRAPHIC ENGINE MONITOR) ON NR 4 CYLINDER AND RICHEN UP MIXTURE TO MAINTAIN COOLER CHT. MAINTENANCE PERSONNEL DISCOVERED 0/80 DURING COMPRESSION TEST AND REMOVED AFFECTED CYLINDER ONLY TO FIND THAT 408 - [SDR CA050318002](https://openairdocs.org/sdr/CA050318002.md): Structure · departed · Jan 27, 2005 · Found FBA2C · Horizontal Stabilizer Structure > (CAN) AC HAD ITS RT FINLET DEPART. AC CONDUCTING REPEAT LATERAL STABILITY TESTING. DEPARTURE WAS BOTH HEARD AND FELT BY PILOT AND TECH OBSERVER. AC RETURNED TO ITS POINT OF DEPARTURE WITH NO ADVERSE STABILITY ISSUES. UPON DETAILED INSP, IT WAS DETERMINED - [SDR CA041117001](https://openairdocs.org/sdr/CA041117001.md): Skin · cracked · Nov 16, 2004 · Found FBA2C · Fuselage Main, Plate/Skin > (CAN) BELLY SKIN CRACKING AT VARIOUS (MULTIPLE POINTS) RIVETS LOOSENING ON INSPECTION COVER SKIN LAP RIVETS LOOSENING. SUSPECTED FROM TURBULENCE CREATED BY PROP INSTALLATION. REPAIRED BY PATCH AND REPLACEMENT OF RIVETS. - [SDR CA041116004](https://openairdocs.org/sdr/CA041116004.md): Hinge Bracket · loose · Sep 24, 2004 · Found FBA2C · Horizontal Stabilizer Structure > (CAN) DURING COMPLETION OF SGB 55-02R1 STABILIZER ATTACHMENT HINGE BRACKET BOLTS FOUND LOOSE (TURN BY FINGERS). - [SDR CA040913004](https://openairdocs.org/sdr/CA040913004.md): Hinge · cracked · Sep 4, 2004 · Found FBA2C · Horizontal Stabilizer Structure > DURING A ROUTINE MX INSPECTION, CRACK WAS DISCOVERED ON THE STABILIZER TRIM HINGE ASSY, (PORT SIDE) P/N: F513-1. TOTAL TIME ON AIRFRAME (AND PART) WAS 802 HOURS. THE CRACK WAS LOCATED BETWEEN THE RADIUS OF THE HINGE ARM AND LIGHTENING HOLE OF HINGE BODY. RE - [SDR CA040623001](https://openairdocs.org/sdr/CA040623001.md): Nut · loose · Jun 21, 2004 · Found FBA2C · Fasteners > (CAN) DURING A ROUTINE INSPECTION THE JAM NUTS THAT SECURE THE PROP CONTROL CABLE TO AN ATTACHMENT BRACKET AT THE PROP GOVERNOR WERE FOUND LOOSE. THE LOWER JAM NUT HAD BACKED OFF COMPLETELY AND THE CABLE WAS FREE TO MOVE, BUT IN ONE DIRECTION ONLY. THE CONTRO - [SDR CA031014004](https://openairdocs.org/sdr/CA031014004.md): Exhaust Valve · cracked · Sep 25, 2003 · Found FBA2C · Reciprocating Engine Cylinder Section > (CAN) EXHAUST VALVE IS BURNED, CRACKED IN TWO PLACES, RADIAL FROM CENTRE. SIDES OF VALVE ARE CHIPPED AND MISSING PIECES. FACE OF ROCKER ARM THAT CONTACTS TOP OF EXHAUST VALVE IS BADLY WORN AWAY. THE HARDENEDFACE IS COMPLETELY GONE AND ARM OF ROCKER ASSEMBLY WA - [SDR CA031014003](https://openairdocs.org/sdr/CA031014003.md): Plug · worn · Sep 25, 2003 · Found FBA2C · Reciprocating Engine Power Section > (CAN) END PLUG IN QUESTION WAS WORN AWAY TO NO MORE THAN.030 OF AN INCH. AT WHICH POINT THE STEEL WRIST PIN WOULD HAVE BEEN WEARING HARDON THE CYLINDER WALL, IF THE ALUMINUM PIN WORE ANYMORE. ALSO NOTED, THE WRIST PIN MOVED ALL THE WAY OVER TOTHE WORN SIDE. - [SDR CA020718010](https://openairdocs.org/sdr/CA020718010.md): Spar · corroded · Jun 28, 2002 · Found FBA2C · Wing Spar > (CAN) WING SPAR CENTRE SECTION LOWER FORWARD CAP ANGLE VERTICAL FLANGE LEG WHERE RIVETED TO SPAR WEB HAS 25 PERCENT LOSS OF THICKNESS IN SEVERAL AREAS PROBABLY DUE TO INTERGRANULAR STRESS CORROSION. NO STRUCTURES REPAIR MANUAL EXISTS FOR THICKNESS LIMITS. ANOT - [SDR CA970904017](https://openairdocs.org/sdr/CA970904017.md): Capacitor · failed · Jun 17, 1997 · Found FBA2C · Magneto/Distributor > (CAN) TWO CAPACITORS FAILED AFTER A SIMILAR SHORT OPERATION. WHEN TESTED ON A DIGITAL CAPACITANCE METER BOTH WOULD GIVE INTERMITTENT IRREGULAR READINGS. NYLON PUSHER BLOCK WAS MELTED ON THE BREAKER POINT SIDE INDICATING EXCESSIVE HEAT BUILD UP, BUT THE CONTACT ## 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 aircraft_model_key = 'FBA2C' ORDER BY difficulty_date DESC ``` This list as a web page: https://openairdocs.org/model/found-fba-2c/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.