# Construcciones Aeronauticas C-212-200 - Type: Aircraft model (FAA registry) - Registry code: 2410312 - Manufacturer (registry): CONSTRUCCIONES AERONAUTICAS SA - Model: C-212-200 - Aircraft type: Fixed wing multi engine - Category: Airplane - Engines: 2 · Turbo-prop - Seats: 48 - Weight class: 20,000 lb and over - Certification: Type certificated - Registered aircraft: 0 - Page: https://openairdocs.org/model/construcciones-aeronauticas-c-212-200 Model codes come from the FAA registry's reference file. ADs are matched to them by model name and maker. ## ADs that may apply (OpenAirDocs) Matched to this model by model name and maker. Each AD's applicability may narrow it by serial number, part number or equipment. None matched. ## Registered aircraft None registered with this model now. ## NTSB investigations None matched to aircraft with this model. ## FAA accident and incident reports None matched to aircraft with this model. ## Service difficulty reports (83, newest 50) As reported by operators and repair stations, by the model named in the report. - [SDR JTAA20260821001](https://openairdocs.org/sdr/JTAA20260821001), Aug 21, 2026: ENGINE. MAKING METAL. NR 2 ENGINE FAILED IN FLIGHT. ON INSPECTION FOUND METAL PARTICLES IN OIL FILTER BOWL. - [SDR UATA2420714265701](https://openairdocs.org/sdr/UATA2420714265701), Jul 8, 2026: RIB. BUCKLED. LEFT WING HAS BUCKLED RIB AND WRINKLED SKIN AT WING STATION 6500. CAUSE/TIMEFRAME OF DAMAGE UNKNOWN. WING APPEARS TO HAVE ENDURED IMPACT ON BOTTOM OF WING TIP A - [SDR UATA2870513265701](https://openairdocs.org/sdr/UATA2870513265701), May 6, 2026: STIFFENER. CRACKED. FOUND A CRACK IN STIFFENER ON THE LH WING FALSE SPAR AT W.S. 4900. THE CRACKED STIFFENER WAS R&R WITH NEW, FABRICATED STIFFENER MADE FROM 2024-T3 ALUMINUM .032" - [SDR UATA2420127265305](https://openairdocs.org/sdr/UATA2420127265305), Jan 27, 2026: FLOORBEAM. COLLAPSED. - F15 WEB SAGGING UNDERFLOOR - REMOVED FRAME15 TOP CAP AND FABRICATED A NEW CAP FROM 2024 T351 ALUMINUM "T" ANGLE, 0.084 THICK, 38.5 INCHES LONG. STRAIGHTENED O - [SDR UATA2420127265304](https://openairdocs.org/sdr/UATA2420127265304), Jan 27, 2026: FLOORBEAM. CORRODED. F16 TOP CAP CORRODED AT NUT PLATES. REMOVED FRAME 16 TOP CAP AND FABRICATED A NEW CAP FROM 2024 T351 ALUMINUM "T" ANGLE, 0.100 THICK. ETCHED AND ALODINED THE "T - [SDR UATA2420127265303](https://openairdocs.org/sdr/UATA2420127265303), Jan 27, 2026: FLOORBEAM. BUCKLED. F12 BUCKLED UNDER FLOOR. F12 UNDERFLOOR T ANGLE CENTER CAP - REMOVED DAMAGED T ANGLE. FABRICATED NEW T ANGLE FROM 2024T3 .085" X 1 5/8" X 1" TO SAME SIZE, DESIG - [SDR UATA2420127265302](https://openairdocs.org/sdr/UATA2420127265302), Jan 27, 2026: FLOORBEAM. CORRODED. F11 CAP CORRODED BETWEEN SEAT RAILS. FL 1 UNDERFLOOR T ANGLE CENTER CAP - REMOVED FRAME 11 CAP SPLICE SECTION. FABRICATED NEW CAP SPLICE SECTION FROM 2024T351 0 - [SDR UATA2026012765301](https://openairdocs.org/sdr/UATA2026012765301), Jan 27, 2026: FITTING. CORRODED. L F11 REAR UNDER FLOOR FITTING CORRODED BEYOND LIMITS, F11 & F6 UNDERFLOOR FITTING HAVE CORROSION AT NUT PLATES. F6 & F11 JUNCTION BAR FITTINGS FOUND CORRODED. - [SDR UATA2420127265701](https://openairdocs.org/sdr/UATA2420127265701), Jan 27, 2026: HINGE BRACKET. CORRODED. RT INBD. FLAP, THE OUTBD. PYLON AIRFRAME SIDE, BOTH OF THE HINGE PLATES HAVE PITTING CORROSION THAT IS BEYOND LIMITS. DRILLED BOTH HINGE PLATES AND THE INBD. AN - [SDR UATA2025121100501](https://openairdocs.org/sdr/UATA2025121100501), Nov 29, 2025: SKIN. CRACKED. RIGHT HORIZONTAL STAB TOP SKIN CRACKED JUST OTBD OF AFT ATTACH FITTING HSS 740. REMOVED TOP REAR SKIN FROM STAB ROOT TO WS 1200. ELEVATOR COVE SKIN WAS DE-RIVIT - [SDR UATA2870815255301](https://openairdocs.org/sdr/UATA2870815255301), Aug 13, 2025: FRAME. BUCKLED. LH FWD FRAME OF THE LOWER RAMP OPENING (P/N 212-23201-03-1) IS BUCKLED BETWEEN FRAME 17+18. REPLACED DAMAGED C CHANNEL 212-23201-03-1 WITH NEW. SEE 337 DATED 08 - [SDR UATA2024092400001](https://openairdocs.org/sdr/UATA2024092400001), Sep 10, 2024: FRAME. BUCKLED. FRAME 16 IS BUCKLED UNDER THE FLOOR JUST LEFT OF CENTER. REMOVED BUCKLED SECTION OF FRAME 16 WEB AND SPLICED IN A NEW PIECE OF MATERIAL. WORK WAS DONE REFERENCI - [SDR UATA2024092402709](https://openairdocs.org/sdr/UATA2024092402709), Sep 10, 2024: ATTACH FITTING. CORRODED. LH HORIZONTAL STABILIZER FORWARD ATTACH FITTING HAS CORROSION AT THE GUIDE PIN HOLE FOR THE TRIANGLE LEADING EDGE. (LOCATED INSIDE THE STABILIZER). REMOVED THE - [SDR UATA2024092405308](https://openairdocs.org/sdr/UATA2024092405308), Sep 10, 2024: FITTING. CORRODED. THE EXTRUSION ON THE AFT SIDE OF FRAME 11 (RIGHT SIDE UNDER FLOOR) HAS INTERGRANULAR CORROSION. REPLACED ORIGINAL FRAME 1 RH AFT FITTING 212-22406-06-2 WITH NEW - [SDR UATA2024092405307](https://openairdocs.org/sdr/UATA2024092405307), Sep 10, 2024: FITTING. CORRODED. THE EXTRUSION ON THE AFT SIDE OF FRAME 6 (RIGHT SIDE UNDER FLOOR) HAS INTERGRANULAR CORROSION. REPLACED ORIGINAL FRAME 6 RH AFT FITTING 212-22406-07-1 WITH NEW - [SDR UATA2024092405306](https://openairdocs.org/sdr/UATA2024092405306), Sep 10, 2024: FITTING. CORRODED. THE EXTRUSION ON THE FWD. SIDE OF FRAME 6 (RIGHT SIDE UNDER FLOOR) HAS INTERGRANULAR CORROSION. REPLACED ORIGINAL FRAME 6 RH FWD FITTING 212-22406-06-1 WITH NEW - [SDR UATA2024092405305](https://openairdocs.org/sdr/UATA2024092405305), Sep 10, 2024: FITTING. CORRODED. THE EXTRUSION ON THE FWD. SIDE OF FRAME 6 (LEFT SIDE UNDER FLOOR) HAS INTERGRANULAR CORROSION. REPLACED ORIGINAL FRAME 6 LH FWD FITTING 212-22406-06-2 WITH NEW - [SDR UATA2024092405304](https://openairdocs.org/sdr/UATA2024092405304), Sep 10, 2024: FITTING. CORRODED. THE EXTRUSION ON THE AFT SIDE OF FRAME 6 (LEFT SIDE UNDER FLOOR) HAS INTERGRANULAR CORROSION. REPLACED ORIGINAL FRAME 6 LH AFT FITTING 212-22406-07-2 WITH NEW R - [SDR UATA202409245303](https://openairdocs.org/sdr/UATA202409245303), Sep 10, 2024: FRAME. BUCKLED. FRAME 16 IS BUCKLED UNDER THE FLOOR JUST LEFT OF CENTER. REMOVED BUCKLED SECTION OF FRAME 16 WEB AND SPLICED IN A NEW PIECE OF MATERIAL. WORK WAS DONE REFERENCI - [SDR UATA202409245302](https://openairdocs.org/sdr/UATA202409245302), Sep 10, 2024: FRAME. CRACKED. ONE PROFILE AT FRAME 10 IS CRACKED AT THE TOP END AND THE FRAME IS BUCKLED (UNDER FLOOR). REPLACED PROFILE, STRAIGHTENED FRAME, AND INSTALLED FRAME DOUBLER. FAA - [SDR UATA2024092405701](https://openairdocs.org/sdr/UATA2024092405701), Sep 10, 2024: PROFILE. CRACKED. L/H OUTBOARD WING HAS ONE CRACKED PROFILE ON THE FALSE SPAR AT WING STATION 4900. REPLACED CRACKED PROFILE WITH ONE OF LOCAL MANUFACTURE. - [SDR 2020F00439](https://openairdocs.org/sdr/2020F00439), Nov 4, 2020: FRAME ANGLE. CORRODED. DURING ROUTINE INSPECTION, ON FRAME 6 UNDER THE FLOORBOARDS AT APPROXIMATELY BL 700(LT), THE FRAME ANGLE WAS FOUND CORRODED WITH A SUBSEQUENT CRACK IN THE SUPPO - [SDR BIGA20200701003](https://openairdocs.org/sdr/BIGA20200701003), Jun 29, 2020: TERMINAL. LOOSE. DURING FLIGHT INTO ICING CONDITIONS THE WINDSHIELD HEAT WAS SELECTED ON AND THE POWER TERMINAL OF THE COPILOT’S WINDSHIELD EXHIBITED ARCING. WINDSHIELD HEAT WAS - [SDR UATA2421209495701](https://openairdocs.org/sdr/UATA2421209495701), Dec 4, 2019: PROFILE. CRACKED. IN COMPLYING WITH AD98-12-28, FOUND ONE FALSE SPAR PROFILE TO BE CRACKED. REPLACED PROFILE WITH A NEW FABRICATED PROFILE. - [SDR BIGA20190821001](https://openairdocs.org/sdr/BIGA20190821001), Aug 18, 2019: LINE. LEAKING. INITIAL REPORTS WERE OF AN SMOKE IN THE COCKPIT, NOTICED HYDRAULIC FLUID ON THE WINDOWS INTERNALLY AND EXTERNALLY AND HYDRAULIC FLUID FROM THE RADOME TO THE RAM - [SDR 39LA20190611184](https://openairdocs.org/sdr/39LA20190611184), Jun 11, 2019: SKIN. CORRODED. DURING SCHEDULED INSPECTIONS, A CORROSION WAS FOUND ON THE CENTER WING UPPER SKIN, R/H WS1175 TO WS3500 . ASSEMBLY OF A TECHNICAL DATA PACKAGE IS CURRRENTLY IN - [SDR 39LA20190611183](https://openairdocs.org/sdr/39LA20190611183), Jun 11, 2019: SKIN. CORRODED. DURING SCHEDULED INSPECTIONS, A CORROSION WAS FOUND ON THE CENTER WING UPPER SKIN, L/H WS1175 TO WS3500 . ASSEMBLY OF A TECHNICAL DATA PACKAGE IS CURRRENTLY IN - [SDR 39LA2019061105182](https://openairdocs.org/sdr/39LA2019061105182), Jun 5, 2019: SKIN. PUNCTURED. DURING SCHEDULED INSPECTIONS, A PUNCTURE WAS FOUND IN THE FUSELAGE SKIN JUST FORWARD OF THE TAIL STAND MOUNT. ASSEMBLY OF A TECHNICAL DATA PACKAGE IS CURRRENTLY - [SDR 39LA2019060311801](https://openairdocs.org/sdr/39LA2019060311801), May 31, 2019: FLOORBEAM. CORRODED. DURING SCHEDULED INSPECTIONS, THE FLOOR BEAM AT LANDING GEAR FRAME 9 WAS FOUND TO HAVE CORROSION AT A FLOORBOARD NUTPLATE. ASSEMBLY OF A TECHNICAL DATA PACKAGE - [SDR 39LA20181030178](https://openairdocs.org/sdr/39LA20181030178), Oct 30, 2018: CHANNEL. CORRODED. DURING REPAIR ACTIONS TO THE RT INBD FLAP PIVOT CONTROL POINT, THE CHANNEL ATTACHED TO THE SUPPORT BOX WAS FOUND TO BE CORRODED. REF SRM FIG 2-24 POS 3 DWG 212- - [SDR 39LA20181030177](https://openairdocs.org/sdr/39LA20181030177), Oct 30, 2018: FITTING. WORN. DURING INSPECTION, DANAGE WAS NOTED TO THE RT INBD FLAP PIVOT CONTROL POINT. THE LT AND RT FITTING PLATES WERE FOUND WORN BEYOND LIMITS AT THE BOLT HOLES. REF S - [SDR KGBR201809240001](https://openairdocs.org/sdr/KGBR201809240001), Sep 24, 2018: SCREW. LOOSE. DURING PANEL REMOVAL FOR INSPECTION. PANEL HOLDING PRESSURE RELIEF VALVE PN:1604270 DISCOVERED ONE ADJUSTING SCREW LOOSE, SECOND ADJUSTING SCREW MISSING AND LAY - [SDR 39LA20151004145](https://openairdocs.org/sdr/39LA20151004145), Oct 4, 2015: BLADE. CRACKED. DURING POST FLIGHT WALK AROUND, THE FLIGHT CREW DISCOVERED ON THE LT PROPELLER ONE OF THE BLADES WAS CRACKED. - [SDR 39LA20150902142](https://openairdocs.org/sdr/39LA20150902142), Sep 2, 2015: UNKNOWN. FUMES. DURING CRUISE, WHEN HEATER VLV OPENED, THE FLIGHT CREW NOTICED FUMES IN BOTH THE FLIGHT DECK & CABIN. TESTED GEARBOX FOR POSITIVE PRESS & FOUND NORMAL NEGATIVE - [SDR 8EKA20150630001](https://openairdocs.org/sdr/8EKA20150630001), Jun 11, 2015: GOVERNOR. STICKS. PROP GOVERNOR STUCK IN FLIGHT. ACFT RETURNED TO BASE. GOVERNOR FOUND TO BE STICKY. - [SDR 39LA20150326110](https://openairdocs.org/sdr/39LA20150326110), Mar 26, 2015: CAP. CORRODED. RIGHT AILERON END CAP FOUND CORRODED THROUGH, AT COUNTERWEIGHT. REPAIRED IAW COMPANY ENGINEERING ORDER 14022-300. - [SDR 8EKA20150309001](https://openairdocs.org/sdr/8EKA20150309001), Mar 6, 2015: ATTACH BRACKET. CRACKED. DURING PERIODIC SCHEDULED INSPECTION FOUND CRACK IN FWD ATTACHMENT BRACKET FOR THE RT HORIZONTAL STABILIZER INBD LE. - [SDR 39LA20150224109](https://openairdocs.org/sdr/39LA20150224109), Feb 24, 2015: SHAFT. SHEARED. DURING THE WALK AROUND INSPECTION PRIOR TO FLIGHT, MX OBSERVED THAT THE LT & RT ELEVATORS WERE DEFLECTED IN OPPOSITE DIRECTIONS. FURTHER INVESTIGATION REVEALED - [SDR 39LA20150203106](https://openairdocs.org/sdr/39LA20150203106), Feb 3, 2015: LIGHT. MALFUNCTIONED. AT CRUISE FLIGHT DURING NIGHT VISION GOGGLE TRAINING THERE WAS AN ORDER OF SMOKE IN THE FLIGHT DECK. THE COPILOTS SIDE OF THE OVERHEAD PANEL WAS HOT TO THE TOUC - [SDR 39LA2014060900005](https://openairdocs.org/sdr/39LA2014060900005), Jun 9, 2014: PROPELLER. SPLIT. IN CRUISE FLIGHT HEARD A LOUD BANG. SCANNED THE ENG INSTRUMENTS, THE LT TORQUE GAUGE WAS AT 120%, THE LT EGT HAD DROPPED BY APPROXIMATELY 100 DEGREES & THE LT F - [SDR 3RAA20140520001](https://openairdocs.org/sdr/3RAA20140520001), May 19, 2014: GEAR. FAILED. DURING A JUMP RUN, WHILE IN CRUISE, THE LT ENGINE CHIP LIGHT FLICKERED MOMENTARILY & THEN THE ENGINE SHUT DOWN. RETURNED TO THE DEPARTURE & LANDED WITHOUT FURTH - [SDR 39LA2013011800003](https://openairdocs.org/sdr/39LA2013011800003), Jan 17, 2013: INDICATION SYS. MALFUNCTIONED. ON CLIMB OUT, RT ENGINE EGT BEGAN TO FLUCTUATE BETWEEN 200- 400 DEGREES. CLIMB POWER WAS SET PRIOR TO FLUCTUATION, EGT READING WAS ERRONEOUS. POWER REDUCED TO P - [SDR 39LA2013011500013](https://openairdocs.org/sdr/39LA2013011500013), Jan 15, 2013: SENSOR. DIRTY. ON CLIMB OUT, ABOUT 8 MILES FROM DPRATURE, RT ENGINE STARTED TO SURGE BETWEEN 95 -60 PERCENT TORQUE, AND 650- 250 EGT. RETURNED TO DEPARTURE. AS ACFT LEVELED OF - [SDR P4YA2012091200001](https://openairdocs.org/sdr/P4YA2012091200001), Aug 24, 2012: CABLE. SEPARATED. DURING HEAVY CHECK, FOUND NR 1 ENGINE TELEFLEX CABLE DAMAGED/PULLED APART AT THE SWAGE HOUSING. - [SDR EHAA20120824007](https://openairdocs.org/sdr/EHAA20120824007), Aug 24, 2012: GEARBOX. INOPERATIVE. DURING CRUISE AT FL 85, THE NR 2 ENGINE RAPIDLY STARTED TO LOSE POWER AND DISPLAYED INDICATIONS OF FAILURE. THE COPILOT AND I NOTICED A CHANGE IN ACFT AND ENGIN - [SDR EHAA20120731006](https://openairdocs.org/sdr/EHAA20120731006), Jul 31, 2012: ENGINE. POWER LOSS. DURING CLIMB, NR 2 ENGINE EGT DROPPED TO ZERO AND ENGINE LOST POWER. - [SDR KGBR2012070600001](https://openairdocs.org/sdr/KGBR2012070600001), Jul 6, 2012: SPAR. CORRODED. LT WING, UPPER FWD SPAR AFT HORIZONTAL LEG, EXFOLIATED AT APPROX WS 3496, ALSO PROBABLE EXFOLIATION AT WS 2130 TO 2450 AND POSSIBLE EXFOLIATION AT WS 2900 TO 30 - [SDR 3RAA2012212001](https://openairdocs.org/sdr/3RAA2012212001), Mar 29, 2012: MOUNT BRACKET. BROKEN. DURING CLIMB AFTER TAKEOFF, THE PILOTS RUDDER PEDALS MOVED ALL THE WAY FORWARD. THE COPILOT TOOK OVER AND SAFELY LANDED THE AIRCRAFT. MAINTENANCE INVESTIGATED A - [SDR STZA2011F00151](https://openairdocs.org/sdr/STZA2011F00151), Jun 23, 2011: WIRE HARNESS. CORRODED. PRIMARY LT FUEL BOOST PUMP LOST POWER. ACFT SAFELY RETURNED TO ORIGINATING AIRPORT. FOUND THAT THE PUMP WIRE HARNESS (THE INTEGRAL WIRES FROM THE PUMP TO THE CO - [SDR BIGASDR1103](https://openairdocs.org/sdr/BIGASDR1103), May 2, 2011: PLATE. CRACKED. AFTER START UP AND ATTEMPTING TO TAXI THE LT AND RT BRAKES WOULD NOT RELEASE PROPERLY AFTER HAVING THE PARKING BRAKE SET. BOTH BRAKE ASSEMBLIES (PN 5006484-3) W All 83: https://openairdocs.org/model/construcciones-aeronauticas-c-212-200/reports.md --- 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.