Dehavilland DHC-3
Service difficulty reports · 394
Newest first. General aviation reporting is voluntary.
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 aircraft_model_key = 'DHC3' 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 aircraft_model_key = 'DHC3' 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 CA140123008Attach Fitting · loose(CAN) DURING A CABLE CHANGE SB V3/005 WAS CARRIED OUT ON THE TAILPLANE ACTUATOR LOWER ATTACH LUG. DURING THE INSPECTION, MOVEMENT WAS NOTED BETWEEN THE LUG AND BOX SECTION. THE LUG WAS REMOVED AND IT WAS NOTED THAT THE RIVETS WERE LOOSE.SDR CA140116005Duct · cracked(CAN) DURING A HOT SECTION INSPECTION, THE LARGE EXIT DUCT WAS FOUND CRACKED ALONG THE OUTER SEAM. THE TTSN OF THE ENGINE AND LED IS 546.5 HOURS. THIS OPERATOR HAS HAD SEVERAL PREVIOUS INSTANCES OF CRACKED LED`S.SDR FAA2014011500030Line · corrodedNOSE GEAR FAILED TO EXTEND ON AMPHIBIOUS FLOATS, CONVERTED EDO 7490 FLOATS. WE FOUND A CORROSION HOLE IN A RIGID ALUMINUM HYDRAULIC LINE BETWEEN THE LINE AND A RUBBER SPACER WHERE THE GEAR INDICATION WIRING TY-RAPED TO THE LINE.SDR CA131219017Compressor Wheel · cracked(CAN) DURING A REGULARLY SCHEDULED BOROSCOPE INSPECTION, CRACKS WERE NOTED ON THE CT DISK BLADE ROOTS AT THE L/E. THE DISK HAD A TSN OF 3042.1 AND A CSN OF 6411. THE HOT SECTION WAS SUBSEQUENTLY REPLACED AND SENT FOR FURTHER EVALUATION. A VISUAL INSPECTION COSDR CA130920015Starter Gen · failed(CAN) DURING FLIGHT THE PILOT NOTICED A BURNING ODOR IN THE COCKPIT. AFTER SEVERAL MINUTES THE OVER VOLT PROTECTION TURNED THE GENERATOR OFF LINE. PILOT DIVERTED AND LANDED SAFELY. THE STARTER GENERATOR WAS VISUALLY INSPECTED AND EVIDENCE OF SEVER DISTRESS SDR CA130808003Motor · failed(CAN) PILOT NOTICED AN UNUSUAL BOOST PUMP NOISE AT START UP, SUSPECT INTERNAL GEAR FAILURE IN MOTOR.SDR CA130703002Pushrod · cracked(CAN) ON INSPECTION A CRACK WAS FOUND ON THE RT AILERON PUSHROD APPROXIMATELY .2500" CRACKED, PART REMOVED FROM SERVICE.SDR CA130627011Bar · cracked(CAN) UPON REPLACEMENT OF THE AFT SPREADER BAR, THE FRONT SPREADER BAR WAS FOUND TO BE CRACKED AT THE FLOAT ATTACH POINT. WE DECIDED TO REMOVE 1 FROM ANOTHER SET OF FLOATS TO REPLACE THE CRACKED ON AND FOUND THAT ON CRACKED IN THE SAME LOCATION.SDR CA130531007Pump · failed(CAN) PLASTIC DRIVE COUPLING FAILED. VACUUM PUMP SCHEDULED FOR REPLACEMENT.SDR ERHA20130604001Yaw Damper · activatedAUTOPILOT WAS RECENTLY INSTALLED THAT HAD A YAW DAMPENER AS AN OPTION. UPON THE TAKEOFF ROLL, THE PILOT CLAIMS THAT THE YAW DAMPENER CAME ONLINE, UNCOMMANDED, CAUSING A LOSS OF DIRECTIONAL CONTROL.SDR CA130626002Bellows · distorted(CAN) ENGINE WOULD NOT DEVELOP POWER FROM IDLE. FCU REPAIRED BY REPAIR FACILITY. FCU REINSTALLED AFTER REPAIR, MAINTENANCE UNABLE TO ADJUST IDLE, MIN FLOW. ENGINE WOULD NOT DEVELOP TAKEOFF POWER. UNIT RETURNED AND DISTORTED BELLOWS ASSY FOUND.SDR CA130626003Fitting · cracked(CAN) FLOAT DECK FITTING INSPECTED AND FOUND CRACKED. UNIT REPLACED WITH NEW FITTING. FLEET INSPECTION FOUND ONE OTHER 55-S-618 CRACKED OUT OF A TOTAL OF SIX FITTINGS. ALSO FITTING FOUND CRACKED ONCE REMOVED FROM FITTING.SDR CA130429013Bolt · corroded(CAN) 3 REPLACEMENT WING STRUT ATTACHED BOLTS RECEIVED FROM MFG WITH SIGNIFICANT SURFACE PITTING. PN C3W114-3, 1 AND C3W129-3, 2.SDR CA130425005Pump · failed(CAN) FUEL PRESSURE FLUCUATING IN FLIGHT WITH NR 1 BOOST PUMP RUNNING. PILOT SELECTED NR 2 BOOST PUMP FUEL PRESSURE STABILIZED. MAINTENANCE FOUND NR 1 BOOST PUMP MOTOR UNSERVICEABLE.SDR CA130110011Relay · misinstalled(CAN) AFTER WIRING THE AVIONICS MASTER RELAY, PN MS24192-D1, IAW WITH A LSTC, THE CIRCUIT WAS TESTED AND THE CIRCUIT BREAKER IMMEDIATELY POPPED. UPON INVESTIGATION, IT WAS FOUND THAT THE RELAY WAS WIRED INCORRECTLY DUE TO THE LABELING ON THE RELAY. THE X1 ANSDR CA121206009Spar · cracked(CAN) UPON 100 HR INSPECTION, SEVERAL CRACKS WERE FOUND ON THE WING SPAR FLANGE ANGLE AT THE WING STRUT PICKUP AREA. FURTHER DISASSEMBLY OF THE WING CRACKS WERE FOUND ON A SECOND FLANGE ON THE OTHER SIDE OF THE PICKUP LUG AREA.SDR CA121009012Bracket · broken(CAN) THE PART DESCRIBED IS A FLYING WIRE ATTACHMENT AT THE BASE OF THE LT FLOAT REAR STRUT POSITION. BEFORE THE FIRST FLIGHT OF THE DAY 1. PILOTS NOTICED THE LT REAR FLYING WIRE HANGING LOOSE. THE PILOT THAT FLEW THE ACFT LAST NOTED, HEARD A NOISE DURING CSDR CA120831002Fuel Control · failed(CAN) AIRCRAFT APPLIED POWER FOR TAKEOFF AND ENGINE WOULD NOT ACCELERATE PAST IDLE. FCU REPLACED WITH SERVICEABLE UNIT AND GROUND TESTED SERVICEABLE. NOTE FURTHER PROBLEMS NOTED.SDR CA120829006Bleed Valve · ruptured(CAN) POOR ENGINE PERFORMANCE DUE TO FAILED BLEED AIR VALVE, RUPTURED DIAPHRAM: HIGH NG LOW FUEL FLOW SLIGHTLY HIGH ITT LOW TORQUE.SDR CA120827015Fitting · cracked(CAN) L/T AFT REAR BAR FITTING, PN 12716 FOUND CRACKED DURING 400 HR. SCHEDULED INSPECTION. CRACKS THROUGH A HORIZONTAL PLANE/MAIN ATTACH BOLT HOLE, PROBABLY AS A RESULT OF CORROSION STRESS.SDR ERHA2012F00160G Switch · inoperativeELT G SWITCH WILL NOT ACIVATE DURING TESTING. REMOTE PILOT ACTIVATED SWITCH WORKS INTERMITTENTLY.SDR CA120618006Cylinder · cracked(CAN) AIRCRAFT HAD NOTABLE POWER LOSS WITH VIBRATION. PILOT LANDED FLOAT EQUIPPED ACFT ON LAKE & REPORTED OIL LEAKING FROM CYLINDER EXHAUST SIDE NR 8 CYLINDER. CYLINDER REPLACED & ACFT RETURNED TO SERVICE. REMOVED CYLINDER FOUND CRACKED FROM OIL DRAIN PORTSDR CA120620004Circuit Breaker · burned(CAN) CIRCUIT BREAKER FOUND BURNT. NEW CB INSTALLED & SYS CHECKED SERVICEABLE.SDR CA120530008Elt · false activation(CAN) ACFT PARKED ON APRON, HAD A UNCOMMANDED ACTIVATION OF THE ELT SYSTEM. MAINTENANCE WAS NOTIFIED BY THE RESCUE CORDINATION CENTER. INVESTIGATION REVEALED THAT NO DAMAGE HAD OCCURED AND THE NO SWITCHES HAD BEEN TURNED ON. ELT APPEARED TO ACTIVATE ON IT`S SDR CA120530007Cable · broken(CAN) ON APPROACH THE PILOT IN COMMAND WAS ADJUSTING THE ELEVATOR TRIM WHEN THE THE NOSE SUDDENLY PITCHED DOWN. THE ACFT LANDED SAFELY AND WAS GROUNDED FOR INSPECTION. THE AME DISCOVERED ON INSPECTION THAT THE ELEVATOR TRIM CABLE ON THE REAR SPINDLE HAD BROKSDR CA120509001Strut · cracked(CAN) FOUND 4" CRACK IN CENTER OF BOTTOM WEB OF LEFT STRUT. DIAGRAM SHOWN ON PAPER VERSION SDR FORM.SDR CA120620002Inverter · failed(CAN) NO TORQUE INDICATION. FOUND THAT ACFT INVERTER FOR TORQUE GAUGE FAILED. UNIT R & R WITH NEW UNIT & CHECKED SERVICEABLE.SDR CA120405002Actuator · unserviceable(CAN) A FAILURE OF THE TRIM ACTUATOR, PN C3CF290-9, CAUSED A RUNAWAY TRIM CONDITION DURING THE ACFT INITIAL CLIMB. ADDITIONAL INFORMATION TO BE PROVIDED FOLLOWING INSPECTION OF THE ACFT AND PART INVOLVED. THE TRIM ACTUATOR HAD NOT BEEN GEARED ADEQUATELY AND SDR CA120224011Push-Pull Rod · worn(CAN) SIGNIFICANT WEAR ON THE ELEVATOR TRIM TAB PUSH-PULL ROD.SDR CA120208004Bumper · disintegrated(CAN) DISASSEMBLED ACTUATOR TO REPLACE O-RINGS AND FOUND BUMPER TO BE TOTALLY DISINTEGRATED. BUMPER LOOSENED ITSELF OFF AND PISTON KEPT POUNDING ON BUMPER AS THE SKIS WENT UP AND DOWN. THIS CAUSE THE CONTAMINATION IN THE HYDRAULIC SYS.SDR CA120125015Blade · failed(CAN) ENROUTE AT 2500` THERE WAS A LARGE BANG FOLLOWED BY AN ENGINE FAILURE AND PROP FEATHERING. ENGINE HAD A TSN OF 4318.8 AND A CSN OF 9768 CYCLES AT THE TIME OF FAILURE. A TEARDOWN INSPECTION IS CURRENTLY ON-GOING TO DETERMINE THE CAUSE OF THE FAILURE.SDR CA120115001Engine · power loss(CAN) WHILE ENROUTE, THE ENGINE LOST POWER AND THE PILOT OF THE FLOATPLANE MADE A FORCED LANDING ON WATER. THERE WERE NO INJURIES AND THE AC WAS NOT DAMAGED. IT WAS TOWED TO SHORE WHERE THE ENGINE WILL BE REPLACED. THE OPERATOR HAS YET TO DECIDE WHERE THE ENSDR CA111103012Actuator · contaminated(CAN) FLOAT PLANE OPERATOR, TAILPLANE ACTUATOR ASSY GETS WET, WATER HAS TO BE DRAINED AND BEARINGS REPLACED OCCASIONALLY (ANNUAL).SDR CA111003011Block · loose(CAN) DURING A REPETITIVE STAB TRIM JACK INSPECTION, NOTED THAT THE BOTTOM JACKSCREW MOUNT WAS LOOSE AND WORKING IN ITS FUSELAGE MOUNTING BRACKET. MOUNTING POINT AND BRACKET WAS REMOVED AND DISASSEMBLED AND THE 3 MOUNTING RIVETS AND THE ASSOCIATED HOLES WERSDR CA110930010Bar · corroded(CAN) FLOAT INSTALLATION THE REAR SPREADER BAR EXHIBITED SIGNS OF CORROSION PRODUCT EXITING THE HOLLOW TUBE ASSY. FURTHER INTERNAL INVESTIGATION REVEALED SEVERE CORROSION INTERNALLY IN THE TUBE ASSY, D30511-1. SPREADER BAR REPLACED, FWD SPREADER BAR WAS REPSDR CA110821001Transmitter · failed(CAN) DURING ROUTINE FLIGHT, THE PILOT NOTICED A DROP IN FUEL PRESSURE/FLOW AND IMMEDIATELY, THE ENGINE LOST POWER AND FLAMED OUT. PILOT TRIED TO RE-START THE ENGINE AND USE THE EMERGENCY POWER LEVER WITHOUT SUCCESS. AFTER A SAFE EMERGENCY LANDING ON A LAKESDR CA110817009Cylinder Head · cracked(CAN) VIBRATIONS DURING FLIGHT AT CRUISING SPEED. PRECAUTIONARY LANDING CYLINDER NR 3 WAS FOUND CRACKED AT CYLINDER HEAD LEVEL.SDR CA110809006Cylinder Head · crackedVIBRATIONS PRIOR TO TAKEOFF - PRECAUTIONARY LANDING - VISUAL INSPECTION REVEALED A SEPARATION (CRACK) OF THE CYLINDER HEAD H1.SDR CA110929016Bracket · cracked(CAN) ON VISUAL INSP, THE LOWER RUDDER BRACKET FLANGE EXTRUSION WAS FOUND TO BE CRACKED AT THE REAR RADIUS ADJACENT TO THE RUDDER PUSH PULL ROD END ATTACH POINT. RUDDER REMOVED AND BOTTOM BRACKET, PN C3TR19-5, REPLACED.SDR CA110802008Structure · damagedPILOT REPORTED A RUMBLING NOISE DURING CLIMB WITH FLAPS DEPLOYED TO THE CLIMB POSITION. UPON LANDING, THE TRAILING FLAP WAS FOUND DAMAGED ON INBD SECTION. TRAILING FLAP WAS REPAIRED AND REINSTALLED AND TEST FLIGHT WAS COMMENCED. THE SOUND WAS STILL EVIDENT ASDR CA110711015Circuit Breaker · inoperativeCIRCUIT BREAKER WON`T RESET.SDR CA110622006Starter Gen · failedSTARTER GENERATOR FAILED - ENGINE START ABORTED. REPLACED STARTER GEN WITH SERVICEABLE START GEN - ENGINE START NORMAL - ACFT RETURNED TO SERVICE.SDR CA110516031Control Rod · damagedDURING A ANNUAL INSPECTION, IT WAS FOUND THAT THIS FLAP CONTROL ROD, HAD SUFFERED DAMAGE RESULTING FROM LONG SCREWS PN: AN 509-10-15. AFTER INVESTIGATING, IT WAS DETERMINED THAT THE 2 SCREWS WERE CORRECT IAW THE IPC, DUE TO ITS SHANK LENGTH, BUT WERE REQUIREDSDR CA110509010Engine · failed(CAN) PILOT WAS ABOUT TO TURN FINAL WESTBOUND AT 1500` WHEN A LOUD BANG OCCURRED AND LOTS OF ENGINE VIBRATION, WITH A CONTINUOUS LOUD HUMMING NOISE. PILOT WENT TO GLIDE SPEED OF 85 MPH AND LOOKED AT ENGINE GAUGES AND THE ENGINE SEEMED TO HAVE ROLLED BACK TO MSDR CA110516014Bleed Valve · failedPOWER LOSS DURING CLIMB, PILOT HEARD A LOUD NOISE FOLLOWED BY A SIGNIFICANT POWER LOSS. POWER LEVER WAS PUSHED TO MAX POSITION BUT THE ENGINE DID NOT RESPOND. THE MANUAL OVERRIDE WAS USED AND A SIGNIFICANT AMOUNT OF POWER WAS RECOVERED, WHICH ENABLED A RETURN SDR CA110503005Pump · wrong part(CAN) PUMP ASSEMBLED INCORRECTLY WOULD NOT PUMP FUEL IN THE INSTALLATION AS CONFIGURED BY THE OH SHOP. PUMP INSTALLED IN ACFT THEN R & R DURING SCHEDULED MAINTENANCE AND REPLACEMENT.SDR CA110428011Rod · loose(CAN) REMOVED RUDDER ROD ASSY TO REPLACE FOWARD ROD END AND UPON CLOSER INSPECTION FORWARD ATTACH FITTING RIVETS WERE FOUND TO BE LOOSE. REPLACED LOOSE RIVETS.SDR CA110428010Rod · loose(CAN) RUDDER CONTROL ROD WAS REMOVED TO REPLACE FORWARD ROD END AND UPON CLOSER INSPECTION LOOSE RIVETS WERE FOUND ATTACHING FORWARD ATTACH FITTING. REPLACED LOOSE RIVETS.SDR CA110419011Bracket · corroded(CAN) DURING ANNUAL ACFT INSPECTION, THE DETACHABLE BOTTOM PART OF THE OLD STYLE BRACKET WAS REMOVED FOR INTERNAL INSPECTION. HEAVY CORROSION WAS EVIDENT AND THE PART WAS REJECTED. A NEW STYLE BRACKET, PN C3FS169-11 WAS INSTALLED AND THE ACFT WAS RETURNED TOSDR CA110414008Fitting · damaged(CAN) ON AN AMPHIBIOUS FLOAT EQUIPPED ACFT, THE PILOT REPORTED THAT HE HEARD AND FELT A SLIGHT BANG WHICH FELT LIKE THE WATER RUDDERS HAD FALLEN DOWN AS SOON AS HE LEVELED OFF AFTER TAKE-OFF. AFTER THE INITIAL BANG, THE ACFT FELT AND SOUNDED NORMAL. UPON LAND
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