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 2026FA0000655Ignition Switch · failedAUTO IGNTION SWITCH FAILURE. SWITCH FAILED INTERNALLY.SDR 2026F00175Igniter · burnedIGNITORS BURN THROUGH TO ELECTRICAL LEAD WITHIN 100 HOURS OF USE. HOT TURBINE COMBUSTION GASES ESCAPE THROUGH IGNITOR BODY TO BURN CONNECTION AND IGITOR LEAD. LEAD SEIZES IN PLACE AND CANNOT BE REMOVED WITHOUT BEING DESTROYED. IGNITOR FAILS, IGNITION LEAD SDR 2026FA0000610Fork · crackedCRACKED TAIL LANDING GEAR FORK PART NUMBER C3UT85-3 . CRACK IN CRITICAL AREA OF FORK WHERE FAILURE COULD CAUSE MAJOR DAMAGE TO AIRCRAFT DURING TAKE OFF OR LANDING. ORIGINAL OEM CAST TAIL FORK FAILS AND BREAKS WHICH FORCES TAIL LANDING GEAR WITH TAIL SKI TO COSDR 2026FA0000487Bolt · shearedPILOT REPORTED ON PREFLIGHT THAT THE RH MAIN SKI BOLT WAS LOOSE AND SUSPECTED BROKEN. INSPECTED AND VERIFIED THE MAIN SKI ATTACH BOLT C3US156-3 WAS BROKEN.SDR 2024F00294Breather Tube · misroutedSMOKE IN CABIN. CORRECTIVE ACTION: FOUND ENGINE BREATHER TUBE MIS-ROUTED CAUSING BREATHER VAPORS TO ENTER THE LOWER FUSELAGE.SDR 2023FA0000098Intake Duct · frozenENGINE IS A PT6A-34, VASAR STC FOR THE PRATT AND WHITNEY TURBINE. PILOT REPORTED A SURGE IN THE ENGINE DURING TAKEOFF AND A POWER LOSS. THE ENGINE RECOVERED QUICKLY AFTER THE POWER LOSS. THE AIRCRAFT WAS BEING RELOCATED FROM NOT FAR FROM THE MAIN HANGER, SO THSDR 2022F00374Attach Bolt · crackedMLG SKI ATTACH BOLT CRACKED AND DEFORMED.SDR 2022FA0000508Spar · crackedLEFT ELEVATOR SERVO TAB SPAR ON ELEVATOR AT HINGE ATTACH POINT CRACKED.SDR 2021F00302Fuel Control · failedFUEL CONTROL PERFORMED AN COMMANDED ACCELERATION, OVERSPEED GOVERNOR STOPPED THE OVERSPEED FROM HAPPENING.SDR ERHA2021062300182Tail Wheel · detachedTAILWHEEL ASSEMBLY PN-C3UT144-9 BROKE FREE FROM THE AIRFRAME JUST AFTER TAKE OFF. THE TAILWHEEL ATTACH BOLT HAD BEEN REPAIRED.SDR CA190709014Fuel Control · malfunctioned(CAN) PILOT APPLIED REVERSE POWER TO BACK AWAY FROM THE DOCK. WHEN THE POWER LEVER WAS MOVED BACK TO THE IDLE POSITION, THE ENGINE ACCELERATED UNCONTROLLED. PILOT TRIED TO SLOW THE AIRCRAFT DOWN BY PLACING POWER LEVER BACK INTO BETA RANGE, THE ENGINE DECELERATSDR CA190412006Duct · cracked(CAN) DURING A REGULARLY SCHEDULED BORESCOPE INSPECTION, DAMAGE WAS NOTED ON THE LARGE EXIT DUCT (LED). UPON FURTHER INSPECTION, A CRACK WAS FOUND ON THE INNER LINING AND NUMEROUS CRACKS WERE FOUND ON THE OUTER LINING ALONG THE WELD SEAM. (TC# 20190412006)SDR CA190412007Engine · damaged(CAN) DURING A NON-SCHEDULED HOT SECTION INSPECTION, THE BOLTS (PART NUMBER MS9574-06) SECURING THE CONTAINMENT RING TO POWER TURBINE VANE RING AT FLANGE D WERE FOUND LOOSE. THE LOCKWIRE WAS INTACT, BUT THERE WAS EVIDENCE OF FRETTING FOUND UNDERNEATH THE HEADSSDR CA190227016Fuel Control · failed(CAN) TO INITIATE DESCENT FOR LANDING, THE PILOT BROUGHT BACK THE POWER. AS THE POWER LEVER WAS BROUGHT BACK, POWER (INDICATED AND ACTUAL) STOPPED REDUCING AROUND 40 PSI, THE THROTTLE LEVER WAS ULTIMATELY BROUGHT TO THE IDLE STOP (GATE) WITH THE POWER (INDICATSDR CA190307019Fuel Control · malfunctioned(CAN) PILOT REPORTED THAT THE AIRCRAFT WAS NOT MAKING MAX POWER. ENGINE GROUND RUNS WERE CARRIED OUT AND WAS UNABLE TO OBTAIN MAX NG. ALSO, THE NG WAS NOT STABLE, IT WAS SLOWLY DECELERATING. THE FCU, PART NUMBER 3244786-8-7, WAS CHANGED AND MAX POWER WAS OBTAISDR TQOA2019F00035Bearing · destroyedPILOT REPORTED THAT HE HAD DIFFICULTY MOVING THE RUDDER SO THE PILOT DECLARED AN EMERGENCY LANDING AND LANDING SAFELY. WHILE INSPECTING THE RUDDER SYSTEM, THE BOTTOM BEARING WAS FOUND TO BE IN PIECES WHICH CAUSE EXCESSIVE PLAY WHEN RUDDER WAS IN MOTION.SDR HNAA2016041800100Bulb · inoperativeEMERGENCY LIGHT INOPERATIVE AT 10DF SECOND RED LT. R & R BULB.SDR CA160301016Ignition Lead · worn(CAN) DURING A REGULARLY SCHEDULED INSPECTION, THE LEFT HAND IGNITION LEAD, P/N CH53399-04, WAS FOUND TO BE WORN AT THE IGNITER ATTACHMENT END. THE LEAD HAD 509.2 HOURS SINCE INSTALLATION. THIS OPERATOR HAS HAD NUMEROUS PROBLEMS WITH IGNITION LEADS FAILING.SDR CA160225005Ignition Lead · failed(CAN) DURING A REGULARLY SCHEDULED INSPECTION, THE LEFT HAND IGNITION LEAD, WAS FOUND TO BE WORN AT THE IGNITER ATTACHMENT END. THIS OPERATOR HAS HAD NUMEROUS PROBLEMS WITH IGNITION LEADS FAILING.SDR CA160202009Csu · failed(CAN) CSU (PROPELLER GOVERNOR) ALLOWING PROPELLER RPM TO CHANGE WITH TORQUE CHANGES, AS POWER WAS ADVANCED OR RETARDED THE PROP RPM WOULD RISE OR FALL BY UP TO 75 RPM PRIOR TO THE GOVERNOR CATCHING IT AND GOVERNING RPM. CSU WAS REPLACED WITH A SERVICEABLE UNITSDR CA151125015Hinge · damaged(CAN) AIRCRAFT WAS TAKING OFF FROM WATER. AT ABOUT 50 FT OF ALTITUDE, THE A/C UNEXPECTANTLY SANK AND INDUCED A LEFT HAND ROLL. THE PILOT TOOK ACTION TO MAINTAIN CONTROL AND LANDED SAFELY. UPON CARRYING OUT THE INVESTIGATION, IT WAS FOUND THAT THE INBOARD FLASDR CA151110010Ignition Lead · damaged(CAN) DURING A REGULARLY SCHEDULED INSPECTION, THE LEFT HAND IGNITION LEAD, P/N CH53399-04, WAS FOUND TO BE WORN AT THE IGNITER ATTACHMENT END. THE LEAD HAD 389.5 HOURS SINCE INSTALLATION. THIS OPERATOR HAS HAD NUMEROUS PROBLEMS WITH IGNITION LEADS FAILING.SDR CA151022007Ignition Lead · worn(CAN) DURING A REGULARLY SCHEDULED INSPECTION, THE RIGHT HAND IGNITION LEAD, P/N CH53399-04, WAS FOUND TO BE WORN AT THE IGNITER ATTACHMENT END. THE TIP WAS BENT. THIS OPERATOR HAS HAD NUMEROUS PROBLEMS WITH IGNITION LEADS FAILING.SDR CA151014009G Switch · failed(CAN) DURING THE ELT ANNUAL RECERTIFICATION, BENCH TESTING FOUND THAT THE G-SWITCH FAILED. THERE WERE ALSO TWO SCREWS WITH O - RINGS MISSING AND THE H-SHIELD WAS CRACKED. THIS OPERATOR HAS HAD SEVERAL OTHER ELT G-SWITCHES FAIL BENCH TESTING AND REQUIRED REPLASDR CA150831008Ignition Lead · broken(CAN) DURING A REGULARLY SCHEDULED INSPECTION, THE RIGHT HAND IGNITION LEAD WAS FOUND TO BE BROKEN AT THE IGNITER ATTACHMENT END. THE LEAD HAD A TSN OF 833.9 HOURS. THIS OPERATOR HAS HAD NUMEROUS PROBLEMS WITH IGNITION LEADS FAILING. IT SEEMS TO BE MOSTLY THESDR CA150818009Ignition Lead · worn(CAN) DURING A REGULARLY SCHEDULED INSPECTION, BOTH LEFT AND RIGHT HAND IGNITION LEADS WERE FOUND TO BE WORN AT THE IGNITER ATTACHMENT ENDS.SDR CA150831010Duct · cracked(CAN) DURING A SCHEDULED HOT SECTION INSPECTION, THE LARGE EXIT DUCT (LED) WAS FOUND CRACKED IN MULTIPLE LOCATIONS ALONG THE OUTER SEAM WELD. THE TSO OF THE LED IS 1687.8 HOURS. THIS OPERATOR HAS HAD NUMEROUS PREVIOUS INSTANCES OF CRACKED LED`S.SDR CA150629022Motor · failed(CAN) WHEN NR 2 BOOST PUMP WAS SELECTED, PUMP SOUNDED VERY ROUGH & LABORED. OVERHAULED MOTOR WAS INSTALLED & DEFECT WAS CLEARED.SDR CA150609005Control Wheel · cracked(CAN) UPON ROUTINE INSPECTION, THE RIVETS ON THE STABILIZER CONTROL WHEEL APPEARED LOOSE. REMOVED THE STABILIZER CONTROL WHEEL FOR FURTHER INSPECTION AND FOUND IT TO BE CRACKED AT THE CENTER HUB AT RIVET LOCATIONS. CRACK LENGTH WAS IN A 2" RADIUS FROM RIVET SDR JKGC20150604001Servo · damagedPILOT FELT VIBRATION IN YOKE, MADE PRECAUTIONARY LANDING. RT ELEVATOR SERVO, SERVO CONTROL ROD & ELEVATOR SKINS SUSTAINED DAMAGE.SDR CA150526006Float · leaking(CAN) FUEL CONTINUED TO LEAK FROM ENG CARB AIR BOX DRAIN PIPE AFTER START UP. STUCK FLOAT SUSPECT. CARB REPLACED WITH SERVICEABLE UNIT & GND RUNS & LEAK CHECK COMPLIED WITH, NO FAULT FOUND. FLOAT ON REMOVED CARB METAL TYPE FUEL HAS LEAKED INTO NORMALLY EMPSDR CA150526005Cam · worn(CAN) AT SPRING RUN UP, ENG SOUNDS LIKE TWIN ENG ACFT WITH PROPS OUT OF SYNC. CAM RING EXHAUST TRACK WEAR SUSPECTED AS IS A KNOWN PROBLEM WITH THIS INDICATION. CAM INSPECTED & WEAR FOUND ON 3 OF 4 CAM LOBES OF EXHAUST TRACK. CAM PN 11768 & 9 EXTRACK ROLLERSSDR CA150506008G Switch · failed(CAN) DURING THE G406-4, ELT`S ANNUAL RECERTIFICATION, IT WAS FOUND THAT THE G-SWITCH INTERMITTENTLY FAILED. THIS WAS THE OPERATOR`S 4TH ELT G-SWITCH THAT FAILED BENCH TESTING AND REQUIRED REPLACEMENT IN THE LAST 4 MONTHS.SDR CA150416004Control Rod · bent(CAN) ANNUAL INSPECTION, LT WING, FOUND THE ACTUATING CONTROL ROD FOR FLAP SYSTEM, PN C3CF105-7 WAS BENT, DEFLECT .5", INSIDE WING, NEAR FUSELAGE, JUST BEHIND THE FIBER ROLLER APPROXIMATE 2", IN NORMAL OPERATION THIS SECTION DOESN`T TOUCH THE FIBER ROLLER, NO SDR CA150408030Bolt · loose(CAN) DURING A NON-SCHEDULED HOT SECTION INSPECTION, THE BOLTS SECURING THE CONTAINMENT RING TO POWER TURBINE VANE RING AT FLANGE D WERE FOUND LOOSE. THE LOCK WIRE WAS INTACT, BUT THERE WAS EVIDENCE OF FRETTING FOUND UNDERNEATH THE HEADS OF THE BOLTS. THE BOSDR CA150408029Duct · cracked(CAN) DURING A NON-SCHEDULED HOT SECTION INSPECTION, THE LARGE EXIT DUCT WAS FOUND CRACKED IN MULTIPLE LOCATIONS ALONG THE OUTER SEAM WELD. THE CRACKS TOTALED APPROXIMATELY HALF OF THE CIRCUMFERENCE OF THE LED. THE TSO OF THE LED IS 1887.5 HOURS. THIS OPERATOSDR CA150408026Blade · sheared(CAN) THE PILOT WAS IN A HOLDING PATTERN, WAITING FOR THE LANDING AREA TO CLEAR. THE ACFT WAS AT 1500 FT & AFTER FIVE MINUTES OF CIRCLING, THERE WAS A BIG BANG FROM THE FRONT OF ENG. OIL STARTED TO SPLATTER OVER THE COWLING & WINDSHIELD, THERE WAS A LOUD GRISDR CA150408022Blades · fractured(CAN) SINGLE OTTER ON FLOATS. WHILE ON FINAL TO LAND, THE PROP FEATHERED UNCOMMANDED AND AN AUDIBLE LOUD NOISE WAS HEARD. THE ACFT LANDED SAFELY ON THE WATER AND PILOT NOTICED THE ENGINE WAS STILL RUNNING, BUT NO OIL PRESSURE. THE PILOT SHUTDOWN THE ENGINE. SDR CA141117006Transducer · failed(CAN) TORQUE READING STUCK AT 130 PSI. 2 MINUTES AFTER TAKEOFF, DURING CLIMB, PILOT REPORTED DOUBLE TORQUE GAUGE FAILURE. TORQUE READING WAS STUCK AT 130 PSI. PILOT RETURNED TO BASE AND LANDED SAFELY. TORQUE PRESSURE TRANSDUCER, PN: APTE-548-2250-70D, WAS SDR 2014FA0000600Circuit Breaker · overheatedA WEAK BATTERY CAUSED A CIRCUIT BREAKER IN THE CHARGING SYSTEM TO TRIP. AFTER REDUCING ELECTRICAL LOAD, THE PILOT RESET THE CIRCUIT BREAKER WHICH SUBSEQUENTLY TRIPPED A SECOND TIME. THE CASE OF THE CIRCUIT BREAKER GOT HOT ENOUGH DURING THE EVENT TO RELEASE ASDR CA140731011Spar · cracked(CAN) THE PILOT NOTICED A SLIGHT VIBRATION IN CONTROL COLUMM - UPON INSPECTION WE LOOKED AT THE TAIL AND NOTICED THE OUTBOARD RH ELEVATOR BEARING HOUSING TO BE LOOSE - OUTBOARD FORWARD ELEVATOR SPAR WAS MAJORLY CRACKED AROUND BEARING HOUSING ATTACH POINT AND NSDR CA140623003Fitting · cracked(CAN) VIBRATION IN FLIGHT, FLOWN TO MAINTENANCE. RIGHT HAND/AFT LOWER FLYING WIRE PULL FOUND CRACKED AND FLYING WIRE FOUND LOOSE. WIRE PULL, REPLACED WITH SERVICEABLE UNIT. FLOAT RIGGING ADJUSTED PER P5M 1-3-2 SECTION 2.41.4 LOG ENTRIES COMPLETED.SDR CA140618003Engine · failed(CAN) SHORTLY AFTER TAKEOFF FROM OUR BASE OF OPERATION OUR DHC-3T OTTER ON FLOATS HAD FLAMES SHOOT OUT OF BOTH OF THE EXHAUST STACKS AND THEN THE PROPELLER RAPIDLY SLOWED TO A STOP AND THE AIRCRAFT MADE A SAFE EMERGENCY LANDING ON THE LAKE AND WAS TOWED BACK TSDR CA140617002Shaft · sheared(CAN) AS PILOT ATTEMPTED TO TAXI AWAY FROM DOCK HE REALIZED HE COULDN`T GET OFF THE STOP LOCKS, MEANING HE HAD LITTLE OR NO REVERSE. AIRCRAFT REPAIR SERVICE REMOVED THE PLANE FROM THE WATER & INSPECTED THE PILOTS DEFECT. IT WAS THEN WE HAD REALIZED AFTER TRYSDR JKGC20140530001Trim Tab · destroyedAIRCRAFT 5000 FEET IN TURBULENCE. ELEVATOR TRIM TAB CAME APART CAUSING DAMAGE TO ELEVATOR.SDR ERHA20140327004Steering Unit · faultyTAIL WHEEL STEERING UNIT CAUSES YAW DAMPENER TO TURN ON UN-COMMANDED. TAIL WHEEL STEERING UNIT HAS AN ELEC COIL THAT IS UNPROTECTED BY A DIODE. THE COLLAPSE OF THE ELEC COILS FIELD CAUSES THE SENSITIVE YAW DAMPENER TO TURN ON UN-COMMANDED.SDR ERHA20140321003Steering Unit · faultyTHE ACFT IS EQUIPPED WITH AN ELEC TAIL WHEEL STEERING UNIT, THAT IS CONTROLLED BY THE PILOT BY THE USE OF A TOGGLE SWITCH. THE OFF ACTIVATION OF THE TAIL WHEEL STEERING SWITCH CAUSED THE INSTALLED AUTOPILOT YAW DAMPENER TO TURN ON UN-COMMANDED. THE ACFT WIRISDR CA140224026Duct · cracked(CAN) DURING A NON-SCHEDULED HOT SECTION INSPECTION, THE LARGE EXIT DUCT WAS FOUND CRACKED ALONG THE OUTER SEAM. THE TTSN OF THE LED IS 1073.8 HRS. THIS OPERATOR HAS HAD NUMEROUS PREVIOUS INSTANCES OF CRACKED LEDS.SDR CA140214006Skin · cracked(CAN) UPON COMPLETING WING INSPECTION ACCESS HOLES INSTALLATION 5 CORRUGATED SKINS WERE FOUND CRACKED.SDR CA140214008Spar · corroded(CAN) ON REPLACING WING CORRUGATIONS ON THE WINGS THE FRONT SPAR PLATE AT APPROXIMATELY BS 70 WAS FOUND CORRODED.
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