N352CA
Service difficulty reports · 31
Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first.
Query with SQL
duckdb -csv -c "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 n_number = 'N352CA' AND registry_match = 'registration' ORDER BY difficulty_date DESC"
Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.
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 n_number = 'N352CA' AND registry_match = 'registration' ORDER BY difficulty_date DESC
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
SDR UATA20264105702Skin · corrodedRH INNER FLAP, OUTBOARD PYLON, OUTBOARD SKIN CORRODED. RH INNER FLAP, OUTBOARD PYLON, HINGE FITTINGS AND OUTBOARD SKIN FOUND CORRODED. APPROXIMATE WING STATION 2900. REMOVED DAMAGED FITTINGS AND SKIN. COPIED EXISTING RIVET PATTERNS AND HOLE SIZE TO NEW FITTINGSDR UATA1900410265701Hinge · corrodedRH INBOARD FLAP, OUTBOARD PYLON BOTH FLAP HINGE PLATES CORRODED. RH INNER FLAP, OUTBOARD PYLON, HINGE FITTINGS AND OUTBOARD SKIN FOUND CORRODED. APPROXIMATE WING STATION 2900. REMOVED DAMAGED FITTINGS AND SKIN. COPIED EXISTING RIVET PATTERNS AND HOLE SIZE TO NSDR UATA2025100605301Fairing · crackedFOUND CRACK IN RH WING TO FUSELAGE FAIRING AT FRAME F5. (SEE AOT-C212-53-0001 FOR DETAILS). REPAIRED CRACK DAMAGE AND REINFORCED F5 RH BY INSTALLATION OF SB KIT SB212530055K01. SEE 337 DATED 09/25/2025. FOR FURTHER DETAILS.SDR UATA2024101045310Door Frame · crackedLOWER CARGO DOOR CUTOUT FRAME, LH SIDE "C" CHANNEL HAS A CRACK IN THE UPPER FLANGE JUST AFT OF FRAME 19. INSTALLED AN INTERNAL REINFORCING DOUBLER BEHIND THE CRACK.. SEE FORM 337 FOR DETAILS OF THE REPAIR.SDR UATA202410100001Door Frame · chafedLOWER CARGO DOOR CUTOUT FRAME, RH SIDE "C" CHANNEL HAS 2 CHAFE MARKS IN THE UPPER RADIUS, JUST FWD. OF FRAME 19. BLENDED CHAFFED AREAS AND INSTALLED AN INTERNAL REINFORCING DOUBLER BEHIND THE CHAFFED AREAS. SEE FORM 337 FOR DETAILS OF THE REPAIR.SDR UATA202410105308Frame · mechanic errorMECHANIC INDUCED DAMAGE TO FRAME 11 WEB, UNDER THE FLOOR, 5 INCHES LEFT OF CENTER. DRESSED OUT THE DAMAGED AREA & FABRICATED A DOUBLER 2 1/4 INCH BY 3 INCHES OF 2024 T3 ALUMINUM 0.040 THICK. ETCHED & ALODINED THAN PRIMED WITH SUPPER KOROPON EPOXY PRIMER. INSTASDR UATA202410105307Fitting · corrodedLH SIDE EXTRUSION ON AFT SIDE OF FRAME 11, UNDER FLOOR HAS EXFOLIATION CORROSION. REPLACED EXTRUSION WITH NEW 212-22406-07-2. SEE FORM 337 DATED 9/20/2024 FOR FURTHER DETAIL.SDR UATA202410105306Fitting · corrodedRH SIDE EXTRUSION ON FWD. SIDE OF FRAME 11, UNDER FLOOR IS CRACKED. (BOUNDARY LAYER CORROSION). REPLACED EXTRUSION WITH NEW 212-22406-06-1. SEE FORM 337 DATED 9/20/2024 FOR FURTHER DETAIL.SDR UATA2024101045305Skin · corrodedLOWER LH SKIN BETWEEN FRAME 17 AND 18 CORRODED. REMOVED DAMAGED SKIN, FABRICATED NEW SKIN AND INSTALLED. SEE FORM 337 DATED 9/20/2024 FOR FURTHER DETAIL.SDR UATA2024101045304Frame · crackedFRAME 19 RH CRACKED BEHIND ACTUATOR ATTACH POINT. REMOVED THE OLD REINFORCEMENT DOUBLER REPAIR. FABRICATED A NEW DOUBLER FROM 2024 T3 ALCLAD ALUMINUM 0.050 THICK, 6 INCHES TALLER THAN THE PREVIOUS DOUBLER (10 INCHES TOTAL). ETCHED AND ALODINE THE DOUBLER AND PSDR UATA2024101045303Frame · crackedFRAME 19 CRACKED BEHIND LH ACTUATOR ATTACH POINT. FABRICATED AND INSTALLED NEW LOWER FRAME 19 AND ACTUATOR ATTACH POINT DOUBLER. SEE FORM 337 DATED 9/20/2024 FOR FURTHER DETAILSDR UATA1901010245302Floorbeam · corrodedUNDER SIDE OF THE UPPER "T" FLANGE AT FRAME 11, THERE IS EXFOLIATION CORROSION UNDER THREE DIFFERENT NUT PLATES (CENTER AREA). REMOVED A 21 INCH SECTION OF THE CENTER "T" FLANGE BETWEEN THE TWO FLOOR SEAT TRACKS. FABRICATED A NEW LENGTH OF "T" FLANGE FROM THE SDR UATA1901010245301Skin · damagedLOWER RH SIDE SKIN BETWEEN FRAME 17 AND 18 CORRODED. REMOVED DAMAGED SKIN, FABRICATED NEW SKIN AND INSTALLED. SEE FORM 337 DATED 9/20/2024 FOR FURTHER DETAILSDR 2024F00148Fairing · wornTHE FIBERGLAS FAIRING ON THE FRONT OF THE OB FLAP, IB HINGE ON THE RH WING CAME LOOSE AND CHAFED INTO THE BOTTOM WING SKIN JUST FORWARD OF THE FLAP HINGE. AIRBUS ENGINEERING WAS CONTACTED WITH THE DAMAGE SPECIFICATIONS AND THEY ISSUED REPAIR INSTRUCTIONS UNDESDR UATA202406105701Fairing · looseOB FLAP, IB HINGE FWD FAIRING BECAME LOOSE AND CHAFED INTO THE BOTTOM SKIN OF THE RH WING, JUST FORWARD OF THE HINGE. THE DAMAGE SPECIFICATIONS WERE SENT TO AIRBUS ENGINEERING AND THEY PRODUCED REPAIR INSTRUCTIONS ON ENGINEERING AUTHORIZATION (EA) NUMBER 24E3SDR UATA202401043521Skin · crackedWHILE INSPECTING THE AIRFRAME PER AD2022-17-06, AOT C212-53-0001 AND SB212-53-0055, A CRACK OF 0.719" WAS FOUND ON THE FUSELAGE SKIN IN THE AREA OUTLINED TO BE INSPECTED BY THE AOT. THE OEM HAS BEEN CONTACTED, THE SITUATION REPORTED, AND A REPAIR SCHEME REQUESSDR UATA2021100735214Attach Fitting · crackedL/H ELEVATOR LOWER AFT ATTACH FITTING ON FUSELAGE FOUND CRACKED AFTER ROUTINE NDI INSPECTION COMPLIED WITH. FITTING R&R PER SB212-53-52.SDR UATA071320207800Heat Shield · crackedUPON SCHEDULED INSPECTION, FOUND L/H EXHAUST DUCT SHROUD/HEAT SHIELD CRACKED AT THE O/B AFT END. THE CRACK WAS APPROXIMATELY 6" LONG, AND RAN ALONG A ROW OF RIVETS IN A FORWARD DIRECTION.SDR UATA2020022625305Floorbeam · corrodedFRAME 6 FLOOR BEAM HAS HEAVY MILLED GUSSETS THAT TIE THE FRAME 6 FLOOR BEAM TO THE FRAME 6 SIDE WALL, BOTH FWD AND AFT OF THE BEAM, ON THE LH AND RH SIDES OF THE BEAM. THERE ARE NUT PLATES CLOSE TO THE ENDS OF THE GUSSETS, AND CORROSION WAS FOUND IN THE GUSSESDR UATA2020022625303Floorbeam · corrodedFOUND DEEP CORROSION IN CENTER OF FRAME 11 FLOOR BEAM, APPROXIMATELY 3 INCHES LONG AND 5/8 INCH WIDE. ROUTED OUT CORRODED AREA AND INSTALLED DOUBLER PER OEM SRM.SDR UATA2020022625302Floorbeam · corrodedAPPROXIMATELY 23 INCHES OF FRAME 17F FLOOR BEAM CAP WAS CORRODED ON TOP. REMOVED SECTION OF BEAM CAP AND SPLICED IN WITH SIMILAR CAP MATERIAL. SPLICE WAS MADE PER OEM SRM.SDR UATA2020022625301Floorbeam · corrodedFOUND CORROSION ON THE UPPER SIDE OF FLOOR FRAME 11F IN CENTER OF BEAM. ROUTED OUT CORRODED AREA AND INSTALLED A DOUBLER, .010 THICKER THAN ORIGINAL MATERIALSDR UATA2019112760101Blade · slippedINSPECTION OF THE SLIPPAGE WITNESS STRIPE SHOWED THAT ONE BLADE OF THE PROPELLER SLIPPED ROTATIONALLY IN THE BLADE TO HUB CLAMP, CAUSING THESDR UATA2019072211119Control Cable · frayedFOUND RT FWD UP ELEVATOR CABLE (OUTBOARD) HAS MULTIPLE BROKEN STRANDS. REPLACED CABLE WITH NEW.SDR UATA2019072201119Control Cable · frayedFOUND LT FWD UP ELEVATOR CABLE (OUTBOARD) TO HAVE MULTIPLE BROKEN STRANDS. REPLACED CABLE WITH NEW.SDR UATA201907221119Control Cable · frayedFOUND LH FORWARD RUDDER CABLE TO HAVE MULTIPLE BROKEN STRANDS. REPLACED CABLE WITH NEW.SDR UATA20190071119Control Cable · frayedFOUND RH FWD PRIMARY RUDDER CABLE TO HAVE MULTIPLE BROKEN STRANDS. REPLACED CABLE WITH A NEW CABLE.SDR UATA032820195701Attach Bracket · corrodedDURING A CORROSION PREVENTION & CONTROL PROGRAM INSPECTION, HEAVY CORROSION WAS FOUND ON THE UPPER INBOARD ATTACH ANGLE OF THE LH WING INBOARD FLAP PYLON.SDR Z8R2003F00000Bushing · wornWHILE LANDING, NOSE GEAR HAD EXTREME VIBRATION CAUSING TORQUE ARM PINS TO POP OUT AND DAMAGING THE BUSHINGS.SDR EHA2001F00006Spline Adapter · strippedSTARTER GENERATOR FAILED TO OVER THE ENGINE ON COMMAND. INVESTIGATION REVEALED THE PLASTIC SPLINE ADAPTER HAD STRIPPED OUT ON THE INTERNAL THREADS.SDR EHA2001F00005Spline Adapter · strippedSTARTER GENERATOR FAILED TO TURN OVER THE ENGINE ON COMMAND. INVESTIGATION REVEALED THE PLASTIC SPLINE HAD STRIPPED OUT ON THE INTERNAL THREADS.
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