Pratt & Whitney R-985 series
Service difficulty reports · 78
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 = 'R985' 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 = 'R985' 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 2018FA0000234Drag Link · damagedDRAG LINK BOLT BROKE IN HALF AND BEGAN DISLODGING WHICH WILL EVENTUALLY RESULT IN LANDING GEAR COLLAPSE. PROBABLE CAUSE BENDING FATIGUE FROM LANDING GEAR CYCLES. RECOMMEND REMOVAL AND REPLACEMENT.
NDT INSPECTION OF 3 ADDITIONAL BOLTS REMOVED FROM SERVICE RSDR 2016F00151Pushrod · brokenDURING CRUISE FLIGHT, ENGINE LOST PARTIAL POWER. PILOT TURNED AROUND TO RETURNED, COULD NOT MAINTAIN ALTITUDE, AND LANDED. DURING TAXIING THE ENGINE DIED. PILOT NEVER TRIED TO RESTART ENGINE AND THE AIRCRAFT WAS TOWED. NO VISIBLE DAMAGE TO THE AIRCRAFT. INVESDR 2015FA0000383Fitting · corrodedA FITTING IN THE LT FLOAT HYDRAULIC DISTRIBUTION BLOCK DEVELOPED A HOLE CAUSED BY CORROSION AND FAILED. THIS IN-TURN CAUSED THE HYDRAULIC FLUID TO ESCAPE AND ULTIMATELY A LOSS OF HYDRAULIC PRESSURE.SDR CA150408034Balance Weight · loose(CAN) DURING A REGULARLY SCHEDULED INSPECTION TO REMOVE A CYLINDER & INSPECT THE POWER SECTION, IT WAS NOTICED THAT THE DYNAMIC BALANCE WEIGHTS HAD AN ALMOST .025 GAP WHICH WAS ABLE TO BE PRIED OPEN TO .060. THE LEADING BOLT COULD BE SPUN INDEPENDENTLY OF THESDR CA140724002Cylinder · cracked(CAN) DURING SCHEDULED 100 HR INSPECTION, BROKEN OFF A PIECE OF CYLINDER NR 9 FOUND RESTING IN LOWER COWLING, FURTHER INVESTIGATION FOUND THE UPPER COWLING MOUNT BRACKET C/W REMAINING/BROKEN PIECE OF CYLINDER STILL ATTACHED IN COWL. CYLINDER NR 9 PUSH ROD HOUSDR CA140115007Cylinder Head · separated(CAN) DURING CRUISE, THERE WAS A LOUD BANG FROM THE ENGINE AND THE ACFT LOST POWER. PILOT EXECUTED A FORCED LANDING. UPON INSPECTION, MAINTENANCE FOUND THAT THE HEAD WAS CRACKED ON THE NR 9 CYLINDER. ENGINE TSO AT TIME OF INCIDENT WAS 275.9.SDR J4HC2013F00112Exhaust Stack · burnedEXHAUST SEGMENTS BURNED THROUGH, CONTRIBUTING TO HIGHER THAN NORMAL INTAKE AIR TEMP RESULTING IN REDUCTION OF POWER DETECTED AT RUN UP.SDR CA130418004Bolt · loose(CAN) ENGINE BEGAN TO RUN ROUGH APPROXIMATELY 15 NM SOUTH OF CAM9 AT ALTITUDE OF 500 FT. ENGINE WAS BACKFIRING, ALL ENGINE INSTRUMENTS SHOWED THE PARAMETERS WERE IN THE GREEN, NORMAL, EXCEPT THE CARBUREATOR TEMPERATURE GUAGE WHICH INDICATED A LARGE SPIKE FOLLSDR WM92012F00000Fuel Tank · leakingFRONT FUEL TANK DEVELOPED AN UNDETECTED LEAK VIA A SMALL CRACK IN THE LOWER CORNER NEAR A WELDED REPAIR. FUEL WAS IGNITED POSSIBLY VIA THE EXHAUST INTENSIFIER DURING ENGINE START-UP RESULTING IN A FIRE UNDER THE FLOOR IN THE FOWARD FUEL TANK BAY. RECOMMEND BSDR TQ0A2012F00048Push-Pull Rod · corrodedPUSH/PULL TUBE WAS REMOVED FROM THE ACFT DURING AN ANNUAL INSPECTION AND WAS FOUND TO HAVE SEVERE PITTING AND HOLES THRU THE TUBE. FOUND THE ALUMINUM WAS SEVERLY CORRODED AT THE AREA WHERE IT MATES WITH THE STEEL TUBE. CORROSION WAS SO SEVERE IT CRACKED THE SDR CA110804004Seal · leakingLT MAGNETO SEAL - PART OF BLOWER ASSY APPEARS TO HAVE SHRUNK ALLOWING SEAL TO LEAK IN 4 BOLT HSG PLATE PN 164315. PERHAPS THE ENGINE OIL IS NOT COMPATIBLE WITH THE SEAL MATERIALS. SB 1266 EXPLAINS THIS ASSEMBLY.SDR CA110812002Main Bearing · damagedON INSPECTION OF THE OIL SCREEN IT WAS NOTICED THAT THERE WAS FOREIGN MATERIAL IN THE OIL SCREEN. THIS MATERIAL WAS TAKEN TO AN O/H SHOP FOR ANALYSIS. WE WERE INSTRUCTED TO PULL 1 CYLINDER AND LOOK AT THE THE MAIN BEARING AND NOTICED THAT A PIECE OF IT WAS MSDR 2010FA0001250Attach Bracket · corrodedBOTH LT AND RT FWD HORIZ STABILIZER ATTACH BRACKETS WERE INSTALLED AS PART OF THE AOG AIR SUPPORT WING ANGLE MOD (STC SA01258NY) DURING ANNUAL INSP FOUND HORIZ STABILIZER FWD ATTACH TO BE LOOSE. PART IS ATTACHED TO THE FWD SPAR OF THE HORIZ STABILIZER WITH 2 SDR LAO2010F00000Rod · corrodedELEVATOR CONTROL ROD ASSY WAS REMOVED FROM ACFT DURING AN ANNUAL INSPECTION. UPON INSPECTION A SMALL HOLE WAS FOUND AT THE AFT END OF THE ROD IN THE LOWER WALL OF THE TUBE (LOW POINT) WHERE MOISTURE WOULD LIKELY COLLECT. FURTHER PROBING OF THE AREA SHOWED THASDR H0VC1Cylinder · brokenNR 2 CYLINDER BROKE FREE FROM ENGINE CASE.SDR 2009F00054Spinner · crackedSMALL CRACKS IN BULKHEAD OF SPINNER AT OUTER RADIUS SPINNER CRACKED AT BLADE SHANK CUTOUTS.SDR CA090407010Bracket · cracked(CAN) HORIZ STABILIZER WAS REMOVED FOR UNASSOCIATED MX. LT PICK-UP BRACKET WAS FOUND TO BE CRACKED ON OTBD FACE. DAMAGE IS SIMILAR TO CRACKS DISCUSSED IN TNS SERIES "B" 55, PARAGRAPH 2.1 WITH THE EXCEPTION THAT THIS ACFT IS ALREADY FITTED WITH MOD/627 - MALESDR CA090402009Control Cable · frayed(CAN) CABLE FRAYED AT STN 228 FAIRLEAD.SDR CA090402010Control Cable · frayed(CAN) CABLE FRAYED AT PULLEY AT STN 228.SDR CA090327002Bearing · wrong part(CAN) DURING REBUILD OF THE LT ELEVATOR THE TECH FOUND THE OTBD BRG TO BE THE WRONG SIZE (TOO WIDE) AND MISSING ONE CIRCLIP TO RETAIN BRG IN HSG. BRG WAS REPLACED WITH PROPER BRG AND CIRCLIP.SDR 2008FA0000871Spar · crackedHAVE JUST HAD THE SPAR X-RAY ACCOMPLISHED IAW AD75-27-09 R2. UPON REVIEW OF THE X-RAYS IT WAS DETERMINED THAT THERE WAS A CRACK. IT SEEMS THIS CRACK OF A VERY SIMILAR ONE WAS PREVIOUSLY REPAIRED AND THAT REPAIR IS IN QUESTION AS WELL. (K)SDR HNJ2008F00000Spar · crackedLT AILERON SPAR CRACKED AT CENTER AND OB HINGE BRACKET ATTACH POINTS. POSSIBLY DUE TO TWISTING EFFECT OF AILERON ACTUATOR INSTALLED AT EXTREME IB END OF AILERON. (K)SDR FAA122808001Bolt · shearedDURING THE INVESTIGATION. IT WAS DISCOVERED THAT THE REMAINDER OF THE BOLT FOR NOSE GEAR RETRACT PUSH PULL TUBE TO CANTILEVER ARM FOR DRAG BRACE HAD SHEARED ON (2) DIFFERENT OCCASIONS FOR REASONS UNDETERMINED. THE OPERATOR ALSO OPERATES (2) OTHER VOLPAR TRICSDR CA071214002Hinge Bracket · broken(CAN) FAILURE NOTICED DURING WALK AROUND BY MECHANIC. THE SPIGOT (INTEGRAL PART OF THE HINGE BRACKET) HAD FAILED COMPLETELY, JUST BELOW THE UPPER EDGE OF THE BALANCE WEIGHT ARM. JUDGING BY THE SURFACES THE SPIGOT HAD BEEN BROKEN FOR SOME TIME. EXTREMELY DANGERSDR CA071214003Cable · corroded(CAN) FUEL SELECTOR CABLE VERY BADLY CORRODED, CABLE FAILED WHEN REMOVED. NO LOG BOOKS OR RECORDS AVAILABLE. (TC NR 20071214003)SDR T522007F00000Cylinder Head · crackedNR 2 CYLINDER WAS FOUND TO HAVE A CRACK ALL THE WAY AROUND THE HEAD JUST ABOVE THE SECOND COOLING FIN. (K)SDR CA070607005Relay · failed(CAN) JUST AFTER TAKEOFF, PILOT NOTICED FAINT SMOKE ODOR BUT UNSURE OF SOURCE, CONTINUED. DURING CLIMB WHITE SMOKE CAME IN AROUND RUDDER PEDALS SO PILOT SHUTDOWN ELECTRICS AND PROCEEDED TO LAND AIRCRAFT. AFTER LANDING PILOT NOTICED SMOKE COMING FROM THE ACCESDR TQ0A20070004Cylinder · failedNR 4 CYLINDER FAILURE AND SEPARATION FROM ENGINE CASE. ROUGH ENGINE LANDING AT TAQUAN AIR.SDR 2007FA0000410Tube · brokenTHIS IS THE THIRD NEW MFG INNER TUBE THAT HAS SPLIT ALONG CIRCUMFERENTIAL WELDED SEAMS.SDR 2007FA0000663Control Arm · crackedDURING COMPLIANCE WITH AD 77-19-07 PARA B, DYE PENETRANT INSPECTION REVEALED 2 POSSIBLE DEFECTS, 0.75 INCH AND 0.5 INCH LONG. BOTH INDICATIONS RADIATING FROM THE TAPERED PIN ON THE STARBOARD SIDE OF THE CONTROL ARM. INDICATIONS CONTINUED TO APPEAR AFTER REPESDR CA060925004Piston · cracked(CAN) DURING REGULAR INSPECTION LOW COMPRESSION WAS NOTED ON NR 1 CYL. CYLINDER WAS REMOVED AND PISTON WAS CRACKED. CYLINDER ASSY WAS REPLACED. AIRCRAFT GROUND RUN WAS CARRIED OUT SATISFACTORY. (TC NR 20060925004)SDR 2006FA0000793Spar · corrodedTHE DEFECT IS SEVERE CORROSION IN SPAR TUBE LT SIDE UPPER AT WING STA 90. PROBABLE CAUSE IS EXPOSURE TO MOISTURE OVER AN EXTENDED PERIORD OF TIMEM. RECOMMENDATION TO PREVENT RECURRENCE WOULD BE TO SEAL AND FILL WITH LIN SEED OIL. FURTHER RECOMMENDATION WOULSDR C2XA05SH144Floor Support · corrodedDURING C-CHECK, MAINTENANCE FOUND CENTER OMEGA BEAM CORRODED AT RAMP ANGLE FRM 20. MAINTENANCE REMOVED AND REPLACED CENTER OMEGA BEAM FROM FRMS 19-25 IAW SRM 51-40-02. AIRCRAFT WAS APPROVED TO RETURN FOR SERVICE.SDR 2006FA0000122Transceiver · malfunctionedDURING POST INSTALLATION CHECKS, FOUND THE GDL90 UAT REPORTING CONTINUOUS EXTERNAL FAULT ERROR. NO EXTERNAL FAULTS FOUND. REPLACEMENT OF THE UNIT CORRECTED THE ERROR. (K)SDR PNSA051105Cowling · departedWHILE IN CRUISE FLIGHT THE LT ENGINE COWLING DEPARTED THE AIRCRAFT. THE COWLING'S WAS NOT RECOVERED, FLIGHT WAS OVER WATER. AN UNEVENTFUL LANDING WAS MADE. SINCE THE FLIGHT WAS OVER WATER IT COULD NOT BE DETERMINED WHY THE COWLINGS DEPARTED THE AIRCRAFT.SDR 2005FA0001633Mount · crackedDURING THE REPLACEMENT OF THE AIR DATA COMPUTER. FOUND THE MOUNTING TRAY ASSY CRACKED COMPLETELY ACROSS ON THE OPPOSITE END OF THE THUMBSCREW. AIRCRAFT IS CONFIGURED ON AMPHIBIAN FLOATS. (K)SDR 2005FA0001077Engine · seizedENGINE SEIZED, UNKNOWN CAUSE. (GL11200513505) (K)SDR TQ0A20050001Engine · seizedENGINE SEIZURE DURING CLIMB-OUT. VISUAL INSPECTION OF ENGINE OIL SCREEN AND SUMPS REVEALED STEEL PARTICLES.SDR 2004F00438Track · crackedDURING A SCHEDULED INSPECTION, FOUND THE AIR DATA COMPUTER (ADC) BROKE LOOSE FROM ITS MOUNT. UPON FURTHER INVESTIGATION FOUND THE MOUNTING BRACKET FLANGE CRACKED COMPLETELY OFF THE AIRFRAME STRUCTURE IT WAS RIVETED TO. AFTER REMOVAL OF THE BRACKET, AND FURTHERSDR GJR2004F00000Pump · failedLOSS OF FUEL PRESSURE.SDR GJR2004F00001Pump · inoperativeLOSS OF FUEL PRESSURE.SDR GJR2004F00002Pump · inoperativeLOSS OF FUEL PRESSURE.SDR 031283Tube · bentDURING SCHEDULED INSPECTION, FOUND AFT FUSELAGE TUBES BENT AND CRACKED. THIS AREA HAD BEEN PREVIOUSLY REPAIRED FOR SIMILAR CONDITION. DAMAGE WAS APPARENTLY CAUSED BY TAIL WHEEL LINK STRIKING TUBES AS A RESULT OF UNDER INFLATION OR COLLAPSE OF TAIL WHEEL STRUTSDR 2004FA0000445Hinge Bracket · corrodedINSPECTED ORIGINAL MAGNESIUM IB AILERON HINGE BRACKETS AND FOUND SOME OR ALL OF THE FOLLOWING CONDITIONS: SEVERELY CORRODED BRACKET BODY AROUND MOUNT AND BEARING BOSS. CRACKS SPANNING COMPLETELY ACROSS THE BEARING BOSS AND/OR MOUNTING FEET. PRIMER AND/OR BOSDR 2004FA0000832Display · malfunctionedFOLLOWING THE INSTALLATION OF THE EFIS-SV SYSTEM, THE SOFTWARE WAS LOADED ONTO A SMART MEDIA CARD AND THE SMART MEDIA CARD WAS INSERTED INTO THE INTEGRATED DISPLAY UNIT (IDU). SEVERAL ATTEMPTS WERE MADE TO UPLOAD THE INFORMATION INTO THE SYSTEM. IT WAS DETERSDR 2003FA0001242Contactor · malfunctionedUPON LANDING THE AIRCRAFT, THE LANDING GEAR FAILED TO EXTEND DUE TO A MALFUNCTION OF THE LANDING GEAR MOTOR CONTRACTOR. PROBLEM WAS DUPLICATED WITH THE AIRCRAFT ON JACKS. TAPPING THE CONTACTOR WITH THE LANDING GEAR SELECTOR IN THE DOWN POSITION WOULD OPERATESDR PCZ2003F00000Brace · corrodedDURING A 100 HOUR INSPECTION, THE UPRIGHT VERTICAL BRACE AT STATION 61 IN THE LEFT WHEEL WELL WAS FOUND CORRODED AND CRACKED. THE CORROSION WAS INTERNAL. THE BRACE (TUBULAR) WAS CRACKED COMPLETELY AROUND ITS CIRCUMFERENCE AT TWO PLACES APPROXIMATELY FOUR INCSDR EON2003F00000Lock · fracturedDURING THE 100 HOUR COMPRESSION TEST, THE ENGINE STOPPED BETWEEN TWO POSITIONS OF APPROXIMATELY 60 DEGREES OF PROP ROTATION FROM HARD INTERNAL CONTACT, FURTHER INVESTIGATION REVELLED THAT THE LOCK BAR ON THE NR 4 ROD LINK PIN HAD FRACTURED AND ALLOWED THE ROD SDR CA030605019Engine · making metal(CAN) DURING REGULAR MAINTENANCE INSPECTION METAL WAS FOUND IN THE OIL SCREEN IN SUFFICIENT QUANTITY TO WARRANT ENGINE REMOVAL.SDR W0P2003F00000Rib · corrodedUPON COMPLYING WITH AD, FOUND CORROSION TO HAVE SEVERELY EATEN AWAY THE TIP RIB ON FOUR DIFFERENT ELEVATORS.
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