Lycoming T5317A
Service difficulty reports · 91
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 = 'T5317A' 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 = 'T5317A' 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 CA030910004Spar Cap · cracked(CAN) WHILE DOING A ROUTINE INSPECTION, A 15 INCH CRACK WAS FOUND IN THE ENGINE DECK AT ITS FORWARD END UNDER THE TRANSMISSION TAIL ROTOR OUTPUT AREA. FURTHER INVESTIGATION WAS CARRIED OUT AND FOUND THAT THE SPAR CAP WAS CRACKED. UPON DISSAMBLY FOR THE CAP REPSDR CA021120008Clutch · failed(CAN) PILOT HEARD A LOUD BANG AS HE WAS LOWERING A LOG ONTO LANDING WITH A SLIGHT DROP IN ALTITUDE. THE AIRCRAFT WAS LANDED AND THE MAIN DRIVE SHAFT BETWEEN ENGINE AND TRANSMISSION WAS ROTATED. THE ROTATIONHAD A ROUGH SOUND WHICH WAS REPORTED TO THE AIRCRAFT MSDR CA021119002Drive Shaft · scored(CAN) WHILE DOING A 100 HOUR INSPECTION ON THE BELL 205A-1, THE TAIL ROTOR DRIVE SHAFT ASSEMBLY WAS FOUND SCORED BEYOND LIMITS. THE INSPECTION IS A CLEARANCE CHECK BETWEEN THE T/R DRIVE SHAFT COVER AND THE T/R DRIVE SHAFT. THIS CLEARANCE CHECK IS DUE TO POSSISDR CA021113004Nozzle · unapproved part(CAN) MILITARY PART FOUND INSTALLED ON ENGINE S/N LE-81004. INSTALLED PART MANUFACTURER CODE NUMBER IS 81996, (US MILITARY) IT SHOULD BE 91547. (HONEYWELL OEM) ITEM INSTALLED 7TH MARCH 2001.SDR CA021001002Bearing · cracked(CAN) FOUND A CRACK (ON A DAILY CHECK) ON THE NR 1 TAILBOOM TAIL ROTOR DRIVE SHAFT BEARING SUPPORT, AS INDICATED IN THE DRAWING SENT. THE SUPPORT POSITIONS THE T/R DRIVE SHAFT BEARING HANGAR. THE T/R BEARING HANGAR IS REMOVED EVERY 6 MONTHS OR 600 HOURS. THIS SDR CA020530002Bleed Band · out of adjust(CAN) WHILE WATER BUCKETING A COMPRESSOR STALL OCCURRED. THE PILOT HOVER TAXIED WITH REDUCED POWER TO THE SHORELINE. AT THE SHORELINE HE DROPPED HIS LOAD AND THE AIRCRAFT WAS RETURNED BACK TO STAGING AREA AND A NORMAL ENGINE SHUTDOWN WAS CARRIED OUT. AFTER TSDR CA020306005Barrel · cracked(CAN) NDT REVEALED A 1.5 INCH CRACK ON THE INTERIOR OF THE COARSE THREADED END. THE CRACK IS NOT VISIBLE ON THE EXTERIOR.SDR GDM2002F00000Connector · fireLANDED, PROCEEDED WITH NORMAL SHUTDOWN PROCEDURES. DURING TWO-MINUTE SHUTDOWN, NOTICED GENERATOR CYCLING ON AND OFF, FIRE LIGHT ILLUMINATED MOMENTARILY THEN WENT OUT. FIRE LIGHT CAME ON AGAIN WITH MORE GENERATOR CYCLING. EXITED HELICOPTER WITH ENGINE AT FLISDR CA011012003Cap · cracked(CAN) ON A TURN AROUND CHECK AFTER REFUELING THE AIRCRAFT, AN ENGINEER FOUND A CRACK ON THE EXPOSED SIDE OF THE LEFT BEAM CAP THAT IS LOCATED NEAR THE FORWARD VERTICAL WALL.SDR 20010124CW005Pump · seizedO.O TIME SINCE OVERHAUL, TRANSMISSION OIL PUMP SEIZED MOMENTARILY, ON FIRST STARTUP AFTER INSTALLATION. DAMAGING TRANSMISSION INTERNAL OIL PUMP DRIVE GEAR. NO SHEARSHAFT INCORPORATEN IN OIL PUMP ASSEMBLY. TRANSMISSION HAD TO BE CHANGED, SECOND INSTANCE ON TSDR CA000718019Tail Rotor · missing(CAN) WHILE IN FLIGHT,TAIL ROTOR TIP CLOSURE FROM BLADE S/N A-9612 DEPARTED BLADE. ENSUING, EXTREME VIBRATION, CAUSED PILOT TO LAND IMMEDIATELY, WITHOUT FURTHER DAMAGE TO A/C. INSPECTION OF T/R SHOWED TIP CLOSURE OF BLADE S/N A-9612 TO BE GONE IN ITS ENTIRETYSDR CA991027035Skin · cracked(CAN) CIRCUMFERENTIAL CRACK ON FIRST PANEL AFT OF MOUNTING BRACKET. LEFT SIDE CRACK APPROXIMATELY 1 INCH LONG. MANUFACTURER CONTACTED AND REPAIR IMPLEMENTED.SDR CA990531002Switch · failed(CAN) DURING EXTERNAL HOISTING OPERATIONS, THE HOIST FAILED NEAR THE FULL-UP POSITION. A VISUAL INSPECTION FOUND THE PLUNGER FOR THE FULL-IN LIMIT SWITCH JAMMED IN THE CABLE GUIDE HOUSING OF THE HOIST THEREBY CUTTING POWER TO THE HOIST MOTOR NOT ALLOWING THE SDR CA990707030Engine · misoverhauled(CAN) MILITARY PARTS FOUND INSTALLED AT ENGINE OVERHAUL INSPECTION. NOTE: HISTORY UNKNOWN. TYPE APPROVAL IE26.SDR CA990430008Shield · failed(CAN) ON SHUTDOWN, FOLLOWING A ONE HOUR LEG OF A 3.5 HOUR FLIGHT, A RUBBING NOISE WAS HEARD FOLLOWING SHUTDOWN WHILE DYNAMIC COMPONENTS WERE STILL ROTATING. ON FURTHER INSPECTION, IT WAS NOTED THAT THE TAILPIPE SHIELD HAD DROPPED OUT OF POSITION AND HAD CONTASDR CA981022003Blade · cracked(CAN) ON SCHEDULED MAINT, CRACK ON TOP OF BLADE, 10.25 INCHES LONG FROM TRAILING EDGE FORWARD, 1/3 DISTANCE FROM HUB TO TIP, NEAR 'YELLOW' CENTER OF BALANCE STRIP.SDR CA980930001Bearing · worn(CAN) ON PURGING GREASE FROM MAIN ROTOR GRIPS, OUTGOING GREASE WAS BROWNISH IN COLOR. ON DISASSEMBLY, BEARING CAGE WEARING ON THE INNER RACE. BEARING REPLACED.SDR 98ZZZX4417Carbon Seal · leakingENGINE REMOVED FOR LEAKING NR 2 CARBON SEAL. FOUND FRONT COMPRESSOR SHAFT HAS GRINDER DAMAGE. DAMAGE TO COMP BLADES WITHIN .50 INCH OF BLADE ROOT. RETAINING BOLT LOCK CUPS NOT DEFORMED SUFFICIENTLY INTO BOLT SLOTS TO SAFELY SECURE BOLTS. 1ST STAGE GAS PRODSDR CA980302005Bolt · worn(CAN) PLAY IN RUDDER CONTROL SYSTEM TRACED TO THE CONTROL BOLT CONNECTING THE CONTROL SPRING STRUT ASSY. TO THE PEDAL SYSTEM CONTROL TUBE. BOLT FOUND TO HAVE DEEP GROOVES-ABOUT 25 PERCENT WORN INTO THE SHANK, WHERE THE SPRING STRUT CLEVIS END CONTACTS THE BOLSDR 97ZZZX4895Lockcup · crackedFOLLOWING DISASSEMBLY OF ENGINE FOR METAL CONTAMINATION, DISCOVERED 2 EACH OF THE LOCKCUPS HAD FAILED. CUPS CRACKED AND SPLIT AT THE LOCKING TANGS WHICH ENGAGE THE PLANETARY GEARSHAFTS. THE RETAINING NUTS WHICH THE LOCKCUPS RETAIN, REMAINED IN PLACE AND THE SDR CA971016001Bearing · broken(CAN) RT AFT ENGINE MOUNT BEARING FOUND LOOSE IN THE ENGINE MOUNG FITTING P/N K97211312. ON DISASSEMBLY, ONE OF THE ENGINE MOUNT BEARINGS OUTER RACE HALVES WAS FOUND SPLIT IN TWO. RETAINING LIP WAS FOUND WORN AWAY ALLOWING THE BEARING TO MOVE LATERALLY.SDR CA970716001Tube · chafed(CAN) AIRCRAFT LOST HYDRAULIC POWER. HOSE WAS CLAMPED TO A FLEX HOSE ASSY AND THE RELATIVE MOVEMENT BETWEEN THE TWO ALLOWED THE TUBE TO CHAFE. IN-FLIGHT, THE MASTER CAUTION SHOWED LOW HYDRAULIC FLUID AND THE CREW COULD ALSO SMELL FLUID THAT WAS LEAKING FROM SDR CA970128002Inlet Guide Vane · loose(CAN) NG WAS EXCEEDING 105 PERCENT, SO AIRCRAFT WAS LANDED IMMEDIATELY AND SHUT DOWN. INITIALLY A CAUSE COULD NOT BE FOUND, BUT AFTER FURTHER INVESTIGATION, NOTICED THE VARIABLE INLET GUIDE VANE RETAINING SCREW HAD LOOSENED ENOUGH TO ALLOW THE SPHERICAL BEARISDR 97ZZZX213Gear · pin failedN2 FAILURE OCCURRED. UPON ENGINE DISASSEMBLY AND INSP, FAILURE WAS CAUSED BY LOCK PIN AN 122683 HOLDING BEARING SLEEVE IN GEAR 1-070-062-04 FALLING OUT ALLOWING GEAR POSITION TO CHANGE AND SUBSEQUENT N2 DRIVE TO FAIL. GEAR IS COMPONENT OF CARRIER ASSY 1-070-SDR 97ZZZX347Governor · failedOVERSPEED GOVERNOR FAILED. PILOT WAS FORCED TO JETTISON LONG LINE, HOOKS, AND LOGS. PILOT AUTOROTATED TOWARDS SERVICE LANDING, WENT T EMERGENCY GOVERNOR SETTING, AND LANDED WITH POWER. NO DAMAGE WAS SUSTAINED. ENGINE BEING REPAIRED BY ALLIED SIGNAL.SDR CA961112051Mount · cracked(CAN) DURING ENGINE REMOVAL TO FACILITATE OTHER AIRFRAME RELATED REPAIRS, THE R/H AFT ENGINE MOUNT FITTING WAS FOUND CRACKED.SDR CA961112049Frame · cracked(CAN) DURING A ROUTINE INSPECTION THE AME DISCOVERED 2 HORIZONTAL CRACKS AT STA.115.0, WL 85.0, LBL 15 INCHES. BOTH CRACKS ORIGINATE AT BOLT HOLE AND PROPAGATE OUTBOARD IN A HORIZONTAL DIRECTION LATERALLY ACROSS THE BULKHEAD. MANUFACTURER INDICATED THAT THIS DSDR 96ZZZX5039Engine · oil ventingENGINE WAS VENTING OIL OVERBOARD FROM LARGE VENT LINE CONNECTED TO N1 GEARBOX. ALL POSSIBLE STEPS TO CORRECT WERE NOT SUCCESSFUL. ENGINE WAS REPLACED AUGUST 29, 1996.SDR CA960826066Pump Body · cracked(CAN) PUMP WAS REMOVED TO FACILITATE TRANSMISSION REPLACEMENT WHEN PUMP MOUNTING FLANGE WAS FOUND CRACKED APPROXIMATELY 1 INCH ACROSS THE THINNEST PORTION OF THE FLANGE ADJACENT TO THE 1 O'CLOCK MOUNT HOLESDR CA960716006Exhaust Diffuser · cracked(CAN) DURING A ROUTINE VISUAL INSPECTION OF THE EXHAUST DIFFUSER, WHILE THE TAILPIPE WAS REMOVED, A 0.075 INCH CIRCUMFERENTIAL CRACK FOUND ON THE DIFFUSER MIDCONE BETWEEN THE 12 O'CLOCK STRUT AND THE DIFFUSER MOUNTING FLANGE.SDR CA960716007Blade · cracked(CAN) DURING HELI LOGGING OPERATION THE PILOT NOTICED INCREASED RIGHT PEDAL REQUIRED TO MAINTAIN POSITION. WHEN IT BECAME OBVIOUS THAT WIND CONDITIONS WERE NOT RESPONSIBLE THE HELICOPTER LANDED WHERE IT WAS FOUND THAT THE BLADE HAD A 10" CRACK CHORDWISE ACROSSSDR CA960703012Engine · making metal(CAN) DURING LOGGING OPERATIONS THE FOLLOWING SEQUENCE OF ENGINE CHIP WARNING INDICATIONS WERE RECORDED. THE ENG WAS REMOVED FROM SERVICE AT 299.3 HOURS. 225.0 HRS-MAGNETIC PASTE FOUND ON AGB CHIP DETECTOR. 276.0 HRS-MAGNETIC PASTE & SOME TINY CHIPS WERE FOUNDSDR CA960620005Gearshaft · chipped(CAN) DURING LOGGING OPERATION, ENGINE CHIP WARNING, IMMEDIATE LANDING. CHIP DETECTOR HAD LARGE CHIP ON IT SIMILAR TO GEAR TOOTH. PLANETARY GEARSHAFT CHIPPED AT THE TIP OF THE SUNGEAR DRIVEN SPLINE.SDR CA960604006Diffuser · cracked(CAN)ON ROUTINE INSPECTION, 2 INCH CRACK JUST FORWARD OF THE 12 O'CLOCK STRUT RUNNING CIRCUMFERENTIALLY AROUND THE EXHAUST DIFFUSER MID CONE.SDR CA960412012Shim · misaligned(CAN)HIGH OIL CONSUMPTION. POWER SHAFT SHIMS MISALIGNED AT REINSTALLATION DURING INSPECTION IMMEDIATELY PRIOR TO OCCURRENCE CAUSING HIGH PRESS AIR TO INDUCE VENTING OF GEARBOX.SDR CA960412013Blade · cracked(CAN) BLADES ARE MATCHED PAIRS. BLADE 1 - CHORDWISE CRACKS 10 INCHES LONG AT STN. 19 AND 75. BLADE 2 DIAGONAL CRACK AT STN. 15. CRACKS COULD NOT BEEN SEEN WITH BLADES AT REST AND UNDER OWN WEIGHT. FUTURE INSPECTIONS WILL BE WITH BLADE TIP SUPPORT.SDR GMAL9501021Governor · defectivePILOT REPORTED GOVERNOR DECAY FROM 104 PERCENT NR DOWN TO 97 PERCENT NR DURING HOVER. PROBLEM INTERMITTENT EVERY 3 TO 4 TURNS DURING LOGGING OPERATIONS. (X)SDR GMAL9501022Seal Housing · crackedCIRCUMFERENCE CRACK OF OUTPUT GEAR SHAFT HOUSING IN STEP-DOWN RADIUS OF HOUSING, LEFT AND RIGHT SIDES 2:00 O'CLOCK TO 5:00 O'CLOCK AND 7:00 O'CLOCK TO 10:00 O'CLOCK POSITIONS. (X)SDR GMAL9501024Seal Housing · crackedCIRCUMFERENCE CRACK OF OUTPUT GEARSHAFT SEAL HOUSING IN STEP-DOWN RADIUS OF HOUSING, LEFT AND RIGHT SIDES. (X)SDR GMAL9501025Seal Housing · crackedCIRCUMFERENCE CRACK OF OUTPUT GEARSHAFT SEAL HOUSING IN STEP-DOWN RADIUS OF HOUSING, 2:00 O'CLOCK TO 6:00 O'CLOCK POSITIONS. THIS SEAL RETAINER WAS REPLACED BY LYCOMING AT TOTAL TIME 583.6 ENGINE HOURS. (X)SDR 95ZZZX6245Drive Shaft · defectiveTA-7 FUEL CONTROL, TIP SEAL PUMP EQUIPPED, WAS FOUND TO HAVE WORN SPLINES. PUMP SECONDARY FUEL FLOW REDUCED TO ZERO PPH. PRIMARY PUMP FLOW REMAINED FULLY FUNCTIONAL. DRIVE SHAFT AND MATING PUMP GEAR SET WERE REPLACED WHILE CONTROL WAS RETURNED REPAIRED.
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