# Service difficulty reports: N352CA A list on [N352CA](https://openairdocs.org/aircraft/N352CA.md). Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first. - [SDR UATA20264105702](https://openairdocs.org/sdr/UATA20264105702.md): Skin · corroded · Apr 8, 2026 · N352CA · Casa C212CC · Trailing Edge Flaps > RH 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 FITTING - [SDR UATA1900410265701](https://openairdocs.org/sdr/UATA1900410265701.md): Hinge · corroded · Apr 8, 2026 · N352CA · Casa C212CC · Trailing Edge Flaps > RH 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 N - [SDR UATA2025100605301](https://openairdocs.org/sdr/UATA2025100605301.md): Fairing · cracked · Sep 25, 2025 · N352CA · Casa C212CC · Wing Main, Frame Structure > FOUND 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 UATA2024101045310](https://openairdocs.org/sdr/UATA2024101045310.md): Door Frame · cracked · Oct 10, 2024 · N352CA · Casa C212CC · Fuselage Structure (General) > LOWER 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 UATA202410100001](https://openairdocs.org/sdr/UATA202410100001.md): Door Frame · chafed · Oct 10, 2024 · N352CA · Casa C212CC · Fuselage Main, Structure > LOWER 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 UATA202410105308](https://openairdocs.org/sdr/UATA202410105308.md): Frame · mechanic error · Oct 10, 2024 · N352CA · Casa C212CC · Fuselage Main, Frame > MECHANIC 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. INSTA - [SDR UATA202410105307](https://openairdocs.org/sdr/UATA202410105307.md): Fitting · corroded · Oct 10, 2024 · N352CA · Casa C212CC · Fuselage Miscellaneous Structure > LH 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 UATA202410105306](https://openairdocs.org/sdr/UATA202410105306.md): Fitting · corroded · Oct 10, 2024 · N352CA · Casa C212CC · Fuselage Miscellaneous Structure > RH 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 UATA2024101045305](https://openairdocs.org/sdr/UATA2024101045305.md): Skin · corroded · Oct 10, 2024 · N352CA · Casa C212CC · Fuselage Main, Plate/Skin > LOWER 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 UATA2024101045304](https://openairdocs.org/sdr/UATA2024101045304.md): Frame · cracked · Oct 10, 2024 · N352CA · Casa C212CC · Fuselage Main, Frame > FRAME 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 P - [SDR UATA2024101045303](https://openairdocs.org/sdr/UATA2024101045303.md): Frame · cracked · Oct 10, 2024 · N352CA · Casa C212CC · Fuselage Main, Frame > FRAME 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 DETAIL - [SDR UATA1901010245302](https://openairdocs.org/sdr/UATA1901010245302.md): Floorbeam · corroded · Oct 10, 2024 · N352CA · Casa C212CC · Fuselage Main, Floor Beam > UNDER 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 UATA1901010245301](https://openairdocs.org/sdr/UATA1901010245301.md): Skin · damaged · Oct 10, 2024 · N352CA · Casa C212CC · Fuselage Main, Plate/Skin > LOWER 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 DETAIL - [SDR 2024F00148](https://openairdocs.org/sdr/2024F00148.md): Fairing · worn · Jun 10, 2024 · N352CA · Casa C212 · Wing Miscellaneous Structure > THE 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 UNDE - [SDR UATA202406105701](https://openairdocs.org/sdr/UATA202406105701.md): Fairing · loose · Apr 24, 2024 · N352CA · Casa C212CC · Wing Miscellaneous Structure > OB 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 24E3 - [SDR UATA202401043521](https://openairdocs.org/sdr/UATA202401043521.md): Skin · cracked · Jan 3, 2024 · N352CA · Casa C212CC · Fuselage Main, Plate/Skin > WHILE 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 REQUES - [SDR UATA2021100735214](https://openairdocs.org/sdr/UATA2021100735214.md): Attach Fitting · cracked · Oct 7, 2021 · N352CA · Casa C212CC · Fuselage, Stabilizer Attach Fittings > L/H ELEVATOR LOWER AFT ATTACH FITTING ON FUSELAGE FOUND CRACKED AFTER ROUTINE NDI INSPECTION COMPLIED WITH. FITTING R&R PER SB212-53-52. - [SDR UATA071320207800](https://openairdocs.org/sdr/UATA071320207800.md): Heat Shield · cracked · Jul 8, 2020 · N352CA · Casa C212CC · Engine Collector/Tailpipe/Nozzle > UPON 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 UATA2020022625305](https://openairdocs.org/sdr/UATA2020022625305.md): Floorbeam · corroded · Feb 26, 2020 · N352CA · Casa C212CC · Fuselage Main, Floor Beam > FRAME 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 GUSSE - [SDR UATA2020022625303](https://openairdocs.org/sdr/UATA2020022625303.md): Floorbeam · corroded · Feb 26, 2020 · N352CA · Casa C212CC · Fuselage Main, Floor Beam > FOUND 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 UATA2020022625302](https://openairdocs.org/sdr/UATA2020022625302.md): Floorbeam · corroded · Feb 26, 2020 · N352CA · Casa C212CC · Fuselage Main, Floor Beam > APPROXIMATELY 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 UATA2020022625301](https://openairdocs.org/sdr/UATA2020022625301.md): Floorbeam · corroded · Feb 26, 2020 · N352CA · Casa C212CC · Fuselage Main, Floor Beam > FOUND 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 MATERIAL - [SDR UATA2019112760101](https://openairdocs.org/sdr/UATA2019112760101.md): Blade · slipped · Nov 26, 2019 · N352CA · Casa C212CC · Propeller Blade Section > INSPECTION OF THE SLIPPAGE WITNESS STRIPE SHOWED THAT ONE BLADE OF THE PROPELLER SLIPPED ROTATIONALLY IN THE BLADE TO HUB CLAMP, CAUSING THE - [SDR UATA2019072211119](https://openairdocs.org/sdr/UATA2019072211119.md): Control Cable · frayed · Jul 11, 2019 · N352CA · Casa C212CC · Elevator Control System > FOUND RT FWD UP ELEVATOR CABLE (OUTBOARD) HAS MULTIPLE BROKEN STRANDS. REPLACED CABLE WITH NEW. - [SDR UATA2019072201119](https://openairdocs.org/sdr/UATA2019072201119.md): Control Cable · frayed · Jul 11, 2019 · N352CA · Casa C212CC · Elevator Control System > FOUND LT FWD UP ELEVATOR CABLE (OUTBOARD) TO HAVE MULTIPLE BROKEN STRANDS. REPLACED CABLE WITH NEW. - [SDR UATA201907221119](https://openairdocs.org/sdr/UATA201907221119.md): Control Cable · frayed · Jul 11, 2019 · N352CA · Casa C212CC · Rudder Control System > FOUND LH FORWARD RUDDER CABLE TO HAVE MULTIPLE BROKEN STRANDS. REPLACED CABLE WITH NEW. - [SDR UATA20190071119](https://openairdocs.org/sdr/UATA20190071119.md): Control Cable · frayed · Jul 11, 2019 · N352CA · Casa C212CC · Rudder Control System > FOUND RH FWD PRIMARY RUDDER CABLE TO HAVE MULTIPLE BROKEN STRANDS. REPLACED CABLE WITH A NEW CABLE. - [SDR UATA032820195701](https://openairdocs.org/sdr/UATA032820195701.md): Attach Bracket · corroded · Mar 28, 2019 · N352CA · Casa C212CC · Wing, Attach Fittings > DURING A CORROSION PREVENTION & CONTROL PROGRAM INSPECTION, HEAVY CORROSION WAS FOUND ON THE UPPER INBOARD ATTACH ANGLE OF THE LH WING INBOARD FLAP PYLON. - [SDR Z8R2003F00000](https://openairdocs.org/sdr/Z8R2003F00000.md): Bushing · worn · Mar 11, 2003 · N352CA · Casa C212CC · Nose/Tail Landing Gear Strut/Axle > WHILE LANDING, NOSE GEAR HAD EXTREME VIBRATION CAUSING TORQUE ARM PINS TO POP OUT AND DAMAGING THE BUSHINGS. - [SDR EHA2001F00006](https://openairdocs.org/sdr/EHA2001F00006.md): Spline Adapter · stripped · Jun 28, 2001 · N352CA · Casa C212CC · Starter-Generator > STARTER GENERATOR FAILED TO OVER THE ENGINE ON COMMAND. INVESTIGATION REVEALED THE PLASTIC SPLINE ADAPTER HAD STRIPPED OUT ON THE INTERNAL THREADS. - [SDR EHA2001F00005](https://openairdocs.org/sdr/EHA2001F00005.md): Spline Adapter · stripped · Jun 28, 2001 · N352CA · Casa C212CC · Starter-Generator > STARTER GENERATOR FAILED TO TURN OVER THE ENGINE ON COMMAND. INVESTIGATION REVEALED THE PLASTIC SPLINE HAD STRIPPED OUT ON THE INTERNAL THREADS. ## 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 n_number = 'N352CA' AND registry_match = 'registration' ORDER BY difficulty_date DESC ``` This list as a web page: https://openairdocs.org/aircraft/N352CA/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.