U/A Canada PT6A-21
Service difficulty reports · 310
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 engine_model_key = 'PT6A21' 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 engine_model_key = 'PT6A21' 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 CA040202012Spar · cracked(CAN) NACELLE OB WEB TO SPAR ATTACHMENT CHANNEL CRACKED IN BEND RADIUS ON LOWER END OF CHANNEL. THIS CONDITION EXISTED IN THE SAME AREA ON BOTH NACELLES. CRACKS ARE COMMON IN THESE AREAS ON HIGH CYCLE AIRPLANES. LATER SN AIRCRAFT COME FROM THE FACTORY WITH DOSDR CA040115006Solenoid · sticking(CAN) DURING LOWERING OF THE LANDING GEAR, UNSCHEDULED YAW WAS NOTICED BY THE CREW AND UPON LANDING, THE AIRCRAFT WAS DIFFICULT TO TAXI. THE RUDDER SYSTEM RECEIVES THE INPUT FROM THE RUDDER BOOST SOLENOID. AS THEY ARE LOCATED IN AN UNHEATED AREA OF THE AIRCRASDR CA031118006Bellcrank · interference(CAN) THE FORWARD ELEVATOR BELLCRANK, CABLE LOCK TAB, WAS FOUND TO BE INTERFERING WITH THE LANDING GEAR MOTOR RELAY OUTBOARD MOUNTING BOLT, PREVENTING THE BELLCRANK FROM CONTACTING ITS MAX NOSE UP STOP (ELEVATOR SECONDARY STOPS). THE RELAY MOUNTING BOLT WAS EXSDR CA031118005Duct · cracked(CAN) CRACK DETECTED IN UPPER FORWARD AREA OF THE INLET DUCT EXTENDING FORWARD AND 1 AFT OF THE OUTBOARD RIVET ROW OF THE INLET LIP. THIS EXCEEDED THE SR-KA-00011 LIMITS, REQUIRING DUCT REPLACEMENT. WHEN DISASSEMBLING THE COWL FOR DUCT REPLACEMENT IT WAS NOTSDR 2003FA0001030Spar Cap · crackedDURING COMPLIANCE OF RAYTHEON AD 89-25-10, WING SPAR INSPECTION, A CRACK WAS DISCOVERED IN THE RIGHT WING LOWER WING SPAR CAP.SDR CA031007004Clevis · out of rig(CAN) WHILE ON A TRAINING FLIGHT AND DEMONTRATING AN EMERGENCY GEAR EXTENSION, THE GEAR WAS UNABLE TO BE RETRACTED AFTER EMERGENCY EXTENSION. THE A/C LANDED SAFELY AND WAS PULLED INTO THE HANGAR AND PLACED ON JACKS. MAINTENANCE FOUND THAT THE THICK CARPET PREVSDR CA031006004Rib · cracked(CAN) UPON REMOVAL OF LOOSE SKIN RIVETS (AFT OF BALANCE WEIGHT, OUTBOARD OF HINGE), AN ENLARGED HOLE WAS OBSERVED WITH APPARENT CRACKING OF THE UNDERLYING RIB. UPON FURTHER INVESTIGATION, RIB P/N 50-610000-415 WAS FOUND CRACKED ALONG THE BEND RADIUS IN 3 OUT SDR CA031006006Anti-Ice System · cracked(CAN) THE ENGINE ANTI-ICE INTAKE TUBE HAS BEEN REPLACED TWICE SINCE SERVICE BULLETIN 71-3142 WAS INCORPORATED. OTHER SIMILAR FAILURES HAVE BEEN DOCUMENTED ON THIS AIRCRAFT.SDR CA031006003Switching Unit · failed(CAN) REPORTED FAULTY NR2 RMI COMPASS BEARING, ADF INDICATION ON RMI NR1, NR2 BOTH NEEDLES WITH NO FLAGS. WHEN BOTH RMI S HAVE NEEDLES NR1, NR2 SELECTED TO NAV COMPASS INDICATION ON NR 2 RMI FREEZES NON IT S CURRENT HEADING. NR 2 RMI COMPASS CANNOT BE SLAVED SDR CA030828004Indicator · arced(CAN) PILOT REPORTS (SNAG VERIFIED LATER) LT FUEL QUANTITY INDICATOR FLUCTUATES BETWEEN 1000 & 1400 LBS. (FREQUENCY OF NEEDLE FLUCTUATION RENDERS NEEDLE A BLUR). INSPECTION OF INDICATOR REVEALED WATER MARKS ON LOWER FORWARD FACE OF INDICATOR AND ON REAR OF INDSDR CA030812001Hinge Bracket · worn(CAN) LT ELEVATOR BOLT FOUND LOOSE DURING CHECK. HINGE BRACKET & BOLT EXHIBITED ABNORMAL WEAR. BOLT GROOVED .024 TO A DIAMETER OF .225 & BRACKET HOLES ELONGATED TO .284 & .290, RESULTING IN EXCESSIVE MOVEMENT OF HINGE. INSTALATION OF BOLT IAW MM WITH ONE AN960SDR CA030717001Line · chafed(CAN) DURING A MAINTENANCE GROUND RUN, AND FOLLOWING THE START OF THE RT ENGINE, A HISSING SOUND WAS NOTICED EMITTING FROM BEHIND THE INSTRUMENT PANEL. AFTER FURTHER INVESTIGATION IF WAS FOUND THAT THE INSTRUMENT AIR TUBE HAD BEEN CHAFING ON THE UPPER CORNER OSDR CA030623004Duct · cracked(CAN) WHILE CARRYING OUT A COMPANY CAMPAIGN NOTICE TO INSPECT ENGINE INLET ANTI-ICE DUCTS FOR CRACKS, BOTH ENGINE SHORT LT DUCTS WERE FOUND CRACKED. ONE DUCT WAS CRACKED ON ONE END AND THE OTHER WAS CRACKED AT BOTH ELBOW ENDS. THE DUCTS HAD ACCUMULATED 191.5 HSDR CA030603003Tube · cracked(CAN) DURING DAILY SERVICEABILITY CHECK THE LT ENGINE SHORT ANTI-ICE FLEX TUBES WAS FOUND TO BE CRACKED. THERE WAS NO EVIDENCE OF AN EXHAUST LEAK INSIDE THE COWLING. THE TUBE WAS CRACKED APPROX. HALF OF IT S CIRCUMFERENCE. CRACKED TUBES WAS REPLACED. LT TUBE TSDR CA030603011Drive Gear · failed(CAN) DURING TRAINING FLIGHT, CREW WAS PERFORMING (TOUCH AND GO). AFTER TAKEOFF, CREW RETRACTED FLAPS AND SYS C/B POPPED. INDICATIONS REVEALED THAT RT FLAPS HAD A STAGGER. CREW DECIDED TO DO A FLAPLESS LANDING. ON GROUND FLAP EXT REVEALED THAT TARGET FLAP (RT SDR CA030602008Line · cracked(CAN) DURING INSPECTION THE LT AND RT ENGINE SHORT ANTI-ICE FLEX TUBES WERE FOUND TO BE CRACKED. THERE WAS NO EVIDENCE OF AN EXHAUST LEAK INSIDE THE COWLING. THE TUBES WERE CRACKED APPROX. HALF OF THEIR CIRCUMFERENCE. CRACKED TUBES WERE REPLACED. LT TUBE TTSN SDR CA030515004Tube · grooved(CAN) THIS AC HAS CLEVELAND BRAKE STC INSTALLED. DURING MAIN GEAR RETRACTION AND EXTENSION LT MAIN GEAR FORWARD HYD BRAKE UNIT CONTACTED MAIN FUEL SUPPLY TUBE AND DAMAGED TUBE BY ERODING A TWO-INCH LONG BY ONE-QUARTER INCH WIDE GROOVE IN TUBE WALL. THIS FUEL TSDR 2003FA0000439Fitting · deformedDURING INSPECTION OF THE WING FITTINGS AND BOLTS THE RIGHT REAR WING ATTACH BOLT WAS FOUND TO BE BENT AND THE FITTING WAS DEFORMED. IN THE MFG STRUCTURAL INSPECTION AND REPAIR MANUAL COVERS THE INSTPECTION OF THE BOLTS AND FITTING AREA. THE BOLT AND A CASTINGSDR CA030416001Tube · cracked(CAN) RT OUTBOARD ANTI-ICE FLEX TUBE FOUND CRACKED BOTH TOP AND BOTTOM AT ATTACH ANGLES. REPLACED WITH NEW PART.SDR CA030416002Control Cable · obstructed(CAN) FWD ELEVATOR BELLCRANK, AFT STOP BOLT WAS NOT CONTACTING ITS PROPER STOP. OUTBOARD MOUNTING BOLT FOR MLG MOTOR RELAY WAS INSTALLED THROUGH UNDER FLOOR BULKHEAD WITH SHANK FORWARD & BOLT EXCESSIVELY LONG. ELEVATOR CABLE-LOCKING TAB WAS STRIKING RELAY-MOUNSDR CA030410002Hinge · cracked(CAN) DURING UNSCHEDULED INSPECTION OF THE TAIL. THE ENGINEER CHECKED FOR PLAY IN THE ELEVATOR HORN BEARINGS P/N MS27645-5. UPON CLOSER EXAMINATION THE ENGINEER NOTICED A CRACK IN THE BEARING HOUSING AREA OF P/N 50-524420-4. AFTER REMOVAL OF THE BEARING FROM SDR CA030410003Tube · cracked(CAN) THE COWLINGS WERE REMOVED FROM THE AIRCRAFT FOR SCHEDULED OIL CHANGE. VISUAL INSPECTION CARRIED OUT ON COWLING PRIOR TO REINSTALLATION IDENTIFIED ONE CRACKED COWL ANTI-ICE BLEED AIR TUBE. NEW PARTS WERE INSTALLED. . A FLEET CAMPAIGN INSPECTION IS ONGOINGSDR CA030408004Tube · cracked(CAN) DURING RT ENGINE CHANGE, THE LOWER COWL WAS REMOVED AND BOTH ENGINE INTAKE ANTI-ICE FLEX TUBES WERE FOUND CRACKED. BOTH TUBES (P/N 90-910099-13 AND 90-910099-17) WERE CRACKED GREATER THAN 50 PERCENT OF THERE CIRCUMFERENCE. THERE WAS NO EVIDENCE OF ANY ESDR AKG2003F00000Motor · failedCREW HAD SMOKE IN THE CABIN AT CRUISE FLIGHT. TURNING THE VENT BLOWER OFF CLEARED THE SMOKE FROM THE CABIN. AFTER REMOVEING THE BLOWER ASSEMBLY FROM THE AIRCRAFT INSPECTION FOUND THAT THE MOTOR WAS LOCKED UP AND THE BRUSHES BURNED.SDR CA030401003Gyro · failed(CAN) NR 2 HSI COMPASS CARD FAILES TO DISPLAY TRUE COMPASS HEADING WITH NO FLAG IN VIEW. WHEN FAILED THE NR 2 HSI COMPASS CARD CANNOT BE SLEWED IN EITHER SLAVE OR FREE MODES, AND IS FROZEN ON ONE BEARING. THE PAIRED CROSS SIDE RMI REMAINES SERVICEABLE AND CAN SDR CA030327001Tube · cracked(CAN) ENGINE INTAKE ANTI-ICE TUBES REPLACED AS PER BEECH SB 71-3142. NEW TUBES FOUND CRACKED AT SECOND INSPECTION AFTER SB COMPLIANCE.SDR CA030326001Bushing · seized(CAN) BUSHING INSERTED INTO ELEVATOR TRIM TAB HORNS, BOTH LT AND RT FOUND TO BE INCORRECTLY INSTALLED. BUSHING WAS NOT INSERTED FAR ENOUGH INTO THE HORN. THIS CAUSED THE CLEVIS FORK END TO CLAMP THE OUTER BUSHING AND HORN TAB INSTEAD OF THE INNER BUSHING. THE SDR CA030326003Bushing · seized(CAN) LT & RT ELEVATOR TRIM HORN INNER BUSHINGS HAD TO BE DRIVEN OUT OF INNER BUSHINGS WITH HAMMER AND PUNCH. ONCE REMOVED & MEASURED, INNER BUSHING DIMENSION WAS FOUND TO BE THE SAME AS OUTER BUSHING INNER DIAMETER. THERE WAS NO CORROSION BETWEEN THE 2 BUSHINSDR CA030321007Bushing · corroded(CAN) DURING INVESTIGATION OF ELEVATOR TRIM TAB CLEVIS , BUSHINGS FOUND CORRODED AND SEIZED ON ONE SIDE/ NEW BUSHINGS AND BOLTS ON ORDER. A/C GROUNDEDSDR CA030321008Bushing · corroded(CAN) DURING INVESTIGATION OF ELEVATOR TRIM TAB CLEVIS , BUSHINGS P/N 50-524024-1 FOUND LIGHTLY CORRODED AND LIGHT WEAR. NEW BUSHINGS AND BOLTS ON ORDER. A/C GROUNDEDSDR CA030321009Bushing · corroded(CAN) DURING INVESTIGATION OF ELEVATOR TRIM TAB CLEVIS , BUSHINGS P/N 50-524024-1 AND P/N 90-610010-5 FOUND LIGHTLY CORRODED AND PARTIALY SEIZED . BOLT AND NUTWERE FOUND INSTALLED CORRECTLY WITH THE CORRECT TORQUE. NEW BUSHINGS AND BOLTS ON ORDER. A/C GROUNDESDR CA030326002Actuator · loose(CAN) DURING ELEVATOR TRIM TAB FREE PLAY CHECK THE LT ELEVATOR TRIM TAB ACTUATOR WAS FOUND TO HAVE EXCESSIVE PLAY. MEASURED .031SDR CA030318002Trim Tab · fretted(CAN) SPECIAL INSPECTION CARRIED OUT AS PER CAMPAIGN 681-27-30-015 WHICH MANDATES INSPECTION OF THE ELEVATOR CONTROL TUBE ATTACHMENT TO TRIM TAB. RT TRIM TAB , BUSHING WAS FOUND NOT SEATED ALL THE WAY INTO THE TRIM TAB HORN. THE OUTBOARD SIDE OF THE HORN HAD SDR CA030317009Tube · broken(CAN) AT FLIGHT LEVEL 220, FLIGHT CREW HEARD A LOUD BANG AND EXPERIENCED SIGNIFICANT AIRFRAME VIBRATION. THE A/C CLIMBED APPROXIMATELY 200FT BEFORE CREW WERE ABLE TO STOP ASCENT. EMERGENCY DECLARED, UNSCHEDULED LANDING CARRIED OUT. MAINTENANCE CREW FOUND THE LSDR CA030221006Channel · chafed(CAN) UPPER ELEVATOR CABLE P/N NAS304-34-0753 FOUND INCORRECTLY ROUTED. INSTEAD OF PASSING THROUGH THE LIGHTNING HOLES IN AFT BOX STRUCTURE P/N50-440031-7, THE CABLE WAS ROUTED ABOVE THE STRUCTURE. THIS CAUSED THE ELEVATOR CABLE TO CUT INTO THE CHANNEL ASSY. WSDR CA030210001Tube · cracked(CAN) LT INBOARD ANTI ICE TUBE FOUND CRACKED AT LOWER (COWL) ATTACH POINT .1 INCH FROM ANGLE FITTING. FLEX HOSE ASSY REPLACED WITH NEW PART. NOTE, RECENT INSTALATION IN COMPLIANCE WITH RAYTHEON S/B 71-3142.SDR CA030117005Line · collapsed(CAN) THE TUBING THAT SUPPLIES PNUEMATIC PRESSURE TO THE DEICER BOOTS WAS FOUND COLLAPSED. THIS TUBE IS LOCATED UNDER THE HEAT REGISTER IN THE AFT BAGGAGE COMPARTMENT. IT APPEARS THE TUBING WAS WARM AND COLLAPSED DURING THE DEICE BOOT CYCLE. THE HEATER DUCT SSDR CA030115006Exhaust Stack · cracked(CAN) DURING ROUTINE INSPECTION THE ANTI ICE BOSS ON THE LT EXHAUST STACK P/N 1099500001 WAS FOUND BROKEN OFF WITH THE ANTI ICE FLEX TUBE. THE FLEX TUBE WAS ALSO CRACKED AROUND THE THE LOWER ELBOW.SDR CA030107003Fitting · cracked(CAN) DURING A ROUTINE INSPECTION, AME NOTICED AN OILY STREAK ON THE FITTING. AFTER CLEANING, IT APPEARED TO BE A DEEP SCRATCH. THE AREA WAS CLEANED WITH SOLVENT AND REEXAMINED, WHICH LOOKED LIKE A CRACK. AN NDT. (LIQUID PENETRANT) WAS PERFORMED TO CONFIRM THESDR CA021209005Computer · intermittent(CAN) AUTO PILOT NR 2 - TRIM WHEEL MOVED IN THE WRONG DIRECTION ON TRIM LIGHT/TRIM WHEEL CHECK. LIGHT ILLUMINATION WAS INTERMITTENT.SDR CA021125012Duct · cracked(CAN) DURING INSPECTION THE RT ENGINE COWL WAS REMOVED AND THE FLEXIBLE TUBE THAT DELIVERS EXHAUST AIR TO HEAT THE ENGINE COWL INTAKE WAS DISCOVERED TO BE CRACKED. THE CRACK EXTENDED APPROXI MATELY 1/3 OF THE CIRCUMFERENCE OF THE TUBE.SDR CA021112007Line · gouged(CAN) INTERFERENCE OCCURRING BETWEEN OIL TRANSFER TUBE AND ANTI ICE FLEX LINE CAUSED TWO GOUGES IN OIL TRANSFER TUBE .015 INCH AND .017 INCH DEEP. WALL THICKNESS OF OIL TRANSFER TUBE IS .025 INCH. THE PROBLEM WAS DETECTED AT SCHEDULED INSPECTION. THE PROBABLE SDR CA021031020Tube · cracked(CAN) ANTI ICE FLEX TUBE FOUND CRACKED.SDR CA021121005Duct · cracked(CAN) LOWER FWD ENGINE COWLING FOUND CRACKED.SDR CA021022003Tube · cracked(CAN) ENGINE INLET ANTI-ICE TUBES REPLACED AS PER BEECH SB 71-3142. NEW TUBES FOUND CRACKED AT FIRST INSPECTION AFTER SB COMPLIANCE.SDR CA021030004Tube · cracked(CAN) ENGINE INLET ANTI-ICE TUBES REPLACED AS PER BEECH SB 71-3142. NEW TUBES FOUND CRACKED AT FIRST INSPECTION AFTER SB COMPLIANCE.SDR CA020927004Tube · cracked(CAN) ENGINE ANTI-ICE INTAKE TUBES REPLACED AS PER BEECH SB 71-3142, WERE FOUND CRACKED (NOT SEPARATED) ATFIRST INSPECTION AFTER SB COMPLIANCE.SDR CA021004006Tube · cracked(CAN) ENGINE ANTI-ICE (INTAKE) TUBES REPLACED AS PER SB 71-3142 (BEECH) - NEW TUBES FOUND CRACKED (NOT SEPARATED) AT FIRST INSPECTION AFTER SB COMPLIANCE.SDR CA020927002Tube · cracked(CAN) ENGINE ANTI-ICE INTAKE TUBES REPLACED AS PER BEECH SB 71-3142, WERE FOUND CRACKED AT FIRST INSPECTION AFTER SB COMPLIANCE.SDR CA020903007Bolt · undertorqued(CAN) AFTER LANDING, DISCOVERED BRAKE FLUID LEAKING FROM AFT CALIPER AFT PISTON BORE GUIDE BOLT, CAUSED BY BOLT BEING UNDER TORQUED. PISTON BORE GUIDE BOLT TIGHTENED TO 30 INCH POUNDS PER CLEVELAND MM. BRAKE RESEVOIR TOPPED OFF, BRAKES CHECKED SERVICEABLE.
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