Lycoming T5317A

Service difficulty reports · 91

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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.

SDR CA150818010Shaft · sheared(CAN) SHAFT SHEARED DURING FLIGHT. MOTOR ASSEMBLY REPLACED.Aug 14, 2015 · Bell 212 · Windshield/Door Rain/Ice RemovalSDR CA150713024Hydraulic Line · ruptured(CAN) DURING FLIGHT THE PILOT EXPERIENCED A LOSS OF NR 2 HYD PRESS. PILOT RETURN TO THE BASE AFTER ISOLATING THE SYS. ONCE THE ACFT LANDED SAFELY, THE INVESTIGATION REVEALED THE LINE TO THE PRESS SIDE OF HYD PUMP NR 2 HAD RUPTURED AT THE 90 DEGREE FITTING. Jul 11, 2015 · Bell 205A1 · Hydraulic System, MainSDR CA150316004Blade · cracked(CAN) DURING INSPECTION OF ACFT BLOWER FAN, IT WAS NOTED THAT 4 OF THE FAN BLADES WERE CRACKED AT THE BASE.Mar 15, 2015 · Bell 205A1 · Turbine Engine Compressor SectionSDR CA150225006Shield · leaking(CAN) DURING DAILY INSPECTION, NOTICED THAT THE HANGER BEARING ASSEMBLY GREASE SHIELD WAS LEAKING. UNIT WAS REPLACED WITH SERVICEABLE, GND RUN CARRIED OUT & NO FURTHER FAULTS. ACFT RELEASED.Feb 23, 2015 · Bell 205A1 · Tail Rotor Drive SystemSDR CA131009002Blade · separated(CAN) A SUDDEN MEDIUM FREQUENCY VIBRATION WAS FELT IN FLIGHT. A PRECAUTIONARY LANDING WAS CARRIED OUT. AFTER VISUAL INSPECTION, IT WAS DISCOVERED THAT THE TIP CAP FILLER HAD SEPARATED CAUSING THE VIBRATION. BOTH BLADES WERE REPLACED, THE TAIL ROTOR WAS BALAAug 24, 2013 · Bell 205A1 · Tail Rotor BladesSDR CA130705006Fitting · cracked(CAN) AME WAS PERFORMING POST FLIGHT/DAILY INSPECTION FOLLOWING LAST FLIGHT OF DAY. DURING INSPECTION, A SMALL VERTICAL LINE WAS NOTED ON THE LT LUG OF THE FITTING THROUGH WHICH THE BOLT SECURING THE TAIL ROTOR DRIVE SHAFT FLEXIBLE COUPLING ASSY TO THE F1TTINGJul 3, 2013 · Bell 205A1 · Tail Rotor Drive ShaftSDR CA130116020Panel · inoperative(CAN) DURING TROUBLESHOOTING OF THE FUEL QTY INDICATING SYS FOR A CALIBRATION DEFECT. THE ACFT WAS SUBSEQUENTLY DEFUELED AND THE AME NOTICED THAT THERE WAS NO LOW FUEL LIGHT INDICATION ON THE MASTER CAUTION PANEL. THE PRESS TO TEST FUNCTION FOR THE FUEL LOW LJan 16, 2013 · Kaman K1200 · Instrument PanelSDR CA121206010Mount · loose(CAN) FOUND DURING INSPECTION, THAT ATTACHMENT BOLTS, HAD COME LOOSE. THE INSPECTION WAS CARRIED OUT IAW INSTRUCTIONS FOR AIRWORTHINESS STC SH08-8. ALSO, THE HOLES HAD ELONGATED CAUSING THE FITTING TO MOVE INSIDE THE STRUT ASSEMBLY. MFG DART AEROSPACE, WAS NDec 3, 2012 · Bell 212 · Engine Mount SectionSDR CA120817001Longeron · cracked(CAN) TOP LT LONGERON ON ACFT LOCATED IN AFT COMPARTMENT WAS CRACKED BEHIND DOUBLER ON TOP LT TAILBOOM ATTACHMENT. CRACK WAS FOUND DURING DAILY INSPECTION, MACHINE WAS FLOWN TO ACFT SERVICE CENTER WERE LONGERON WAS REPLACED.Aug 7, 2012 · Bell 205A1 · Fuselage Main, Longeron/StringerSDR CA120817004Tachometer · failed(CAN) CO-PILOT DUAL TACH N2 ENGINE RPM NEEDLE, FLUCUATES FROM 0 TO 50 PERCENT THEN STICKS.Jun 6, 2012 · Bell 205A1 · Engine RPM Indicating SystemSDR CA120223006Cap · fractured(CAN) FAILURE OF CAP, IN ORDER TO EXAMINE THE FRACTURE SURFACE OF A STRUCTURAL LONGERON, HERE-IN REFERRED TO AS A CAP. THE CAP, PN 205-030-207-005 AND THE ASSOCIATED TAILBOOM ATTACHMENT FITTING, PN 205-030-767-005, WERE SUBSEQUENTLY SENT TO FOR EXAMINATION ANDJan 28, 2012 · Bell 205A1 · Rotorcraft Tail BoomSDR CA120116003Gimbal Ring · damaged(CAN) DURING 100 HRS INSPECTION, 2 SMALL DAMAGED SCREWS WHERE FOUND IN THE BOTTOM OF THE MAIN TRANSMISSION BAY STILL ATTACHED WITH LOCKING WIRE. FURTHER INSPECTION REVEALED THAT THE SCREW BELONGED TO 1 OF THE 4 SWASHPLATE GIMBAL RING ATTACHEMENT POINTS. SWASJan 16, 2012 · Bell 205A1 · Main Rotor Mast/SwashplateSDR CA111220005Blade · cracked(CAN) 3 CRACKS DEVELOPED ON BOTTOM SIDE OF BLADE SKIN, PN 212-015-501-115, SN A6009 (TSN) 3521.9, 1 CRACK 5.5", THE OTHER 2 CRACKS ARE 2.5" - 3.5" RESPECTIVELY. MEASURING FROM TRIM TAB EDGE INBD 41.5" IS THE LONG, 5.5. THE OTHER 2 CRACKS ARE OTBD A FEW INCHEDec 20, 2011 · Bell 205A1 · Main Rotor BladesSDR CA110909011Governor · failed(CAN) ACFT LEVELED OFF AFTER CLIMB, A BANG WAS HEARD THEN ACFT YAWED, ROTOR LOW HORN AND LIGHT SOUNDED. ENGINE FAILURE WAS CONFIRMED- N1 WAS AT 25 PERCENT AND TORQUE WAS READING 0. ACFT AUTOROTATED TO GROUND. FUEL CELLS AND AIRFRAME FILTER ON BOARD INSPECTEAug 14, 2011 · Bell 205A1 · Turbine GovernorSDR CA111222011Diffuser · used(CAN) UPON LANDING AND PERFORMING A POST FLIGHT VISUAL INSPECTION THE AME FOUND THE BOTTOM STRUT ON THE EXHAUST DIFFUSER CRACKED WITH A SECTION OF MATERIAL MISSING. THE EXHAUST DIFFUSER SERVES AS THE REAR BEARING SUPPORT. AS A RESULT OF THIS DEFECT THE POWERMar 6, 2011 · Bell 205A1 · Engine Collector/Tailpipe/NozzleSDR CA101122028Baffle · detachedBAFFLE DIVIDING FORWARD AND AFT SECTIONS OF FUEL CELL, FOUND DETACHED. FUEL IS ABLE TO MOVE AROUND POTENTIALLY CAUSING C OF G ISSUES. IN LOW FUEL SITUATIONS, SLOSHING FUEL MAY CAUSE SUPPLY TO THE PUMPS TO DIMINISH, POTENTIALLY CAUSING ENGINE FUEL STARVATION. Nov 22, 2010 · Bell 205A1 · Fuel StorageSDR CA090806005Governor · unknownEXCESSIVE ENGINE DROOP.Jul 30, 2009 · Bell 205A1 · Turbine GovernorSDR CA090702013Fitting · crackedDURING A POST FLIGHT INSP, THE TAIL ROTOR DRIVE FITTING WAS FOUND CRACKED. TIME ON THE FITTING IS UNKNOWN. CRACK WAS FOUND RADIATING FROM THE BORE OF THE BARREL NUT ATTACHMENT. UNSURE IT THIS MAYBE THE CAUSE OF OVER TORQUING OF THE BOLT. NUT WAS REPLACED WJul 1, 2009 · Bell 205A1 · Tail Rotor Drive SystemSDR CA090619003Quill Assy · shearedACFT WOULD NOT START, UPON FURTHER INVESTIGATION THE QUILL DRIVE FROM STARTER/GENERATOR TO ENGINE FOUND SHEARED.Jun 16, 2009 · Bell 205A1 · Starter-GeneratorSDR CA090126003O-Ring · leaking(CAN) REPORTS OF A LOW FUEL CAUTION LIGHT COMING ON EARLY AND SMALL FUEL DRIP PROMPTED MX TO REMOVE THE LT FUEL CELL SUMP PLATE TO INSPECT THE LOW LEVEL FUEL SWITCH/BOOST PUMP AREA AND FACILITATE AN O-RING REPLACEMENT. UPON REMOVAL OF THE SUMP PLATE A T-SHIRT/Jan 25, 2009 · Bell 205A1 · Fuel Boost PumpSDR CA081120004Mount · cracked(CAN) CRACK DISCOVERED ON LT FWD STRUT MOUNT FITTING.Nov 16, 2008 · Kaman K1200 · Main Rotor HeadSDR CA080731002Bearing · rough(CAN) UPON A SCHEDULED INSPECTION OF THE TRANSMISSION WAFFER FILTER AN EXCESSIVE AMOUNT OF FERROUS METAL WAS FOUND. THERE HAD BEEN NO METAL FOUND ON THE CHIP DETECTOR OR IN THE COURSE INLET SCREEN. A SWEEP OF THE SUMP WITH A MAGNET FOUND NO METAL. AFTER DISSASJul 29, 2008 · Bell 205A1 · Main Rotor GearboxSDR CA081023005Fitting · cracked(CAN) WHILE CONDUCTING 100 HR INSP NOTED AREA IN LT LOWER TAIL BOOM LONGERON AT FWD FITTING TO BE CRACKED. NDT CONFIRMED A CRACK INDCATION OF 1.5 INCHES LONG IN THE FITTING.Jul 27, 2008 · Bell 205A1 · Rotorcraft Tail BoomSDR CA080604011Attach Fitting · cracked(CAN) WHILE CONDUCTING A 25 HR INSP, A CRACK WAS NOTED ON THE LIFT LINK BEAM LUG. THE PART WAS REMOVED AND TT OF THE BEAM IS UNKNOWN AT THIS TIME. CRACK WAS FOUND ON THE AFT EAR OF LUG RT SIDE.May 28, 2008 · Bell 205A1 · Fuselage Main, Attach FittingsSDR CA080326001Wire · chafed(CAN) DURING START UP THE STARTER RELAY CIRCUIT BREAKER WAS POPPING NOT ALLOWING THE STARTER TO START. IT WAS FOUND THAT THERE WERE 2 WIRES LABELED K2D20 AND K3C20 CHAFFED INSIDE THE CO-PILOTS COLLECTIVE. K3C20 HAD BEEN SOLDER SPLICED AND CHAFED AT THE SPLICEMar 25, 2008 · Bell 205A1 · Engine Starting System WiringSDR CA080117002Bearing · unserviceable(CAN) FOUND TAIL ROTOR HUB ASSY OB BEARING CAGE INSERT OUT OF IS SOCKET. ASSY SEND FOR O/H. (TC NR 20080117002)Jan 17, 2008 · Bell 205A1 · Tail Rotor HeadSDR CA080124003Crosstube · cracked(CAN) WHILE THE ENGINEER WAS CONDUCTING THE DI, A CRACK IN THE AFT DART CROSSTUBE WAS DISCOVERED. THE DART CROSSTUBE FOLLOWS 300/600 HR INSP CYCLE. CROSSTUBE WAS 60.7 FROM 300 HR INSP, AND 360.7 FROM THE 600 HR. CROSSTUBE WAS CHECKED FOR EXCESSIVE DEFLECTION, Jan 17, 2008 · Bell 205A1 · Main Landing GearSDR CA071214009Mount · cracked(CAN) RT ENGINE BIPOD INSPECTED FOR SUSPICIOUS CRACK IN FRONT TUBING DURING 100 HRS INSPECTION. NDT REVEALED CRACK MOUNT AT WELDED JOINT. NOTE: THIS MOUNT WAS MODIFIED IAW STC SH99-11, DART ADJUSTABLE MOUNT. (TC NR 20071214009)Dec 10, 2007 · Bell 205A1 · Engine Mount SectionSDR CA071127011Fitting · cracked(CAN) ON ROUTINE INSPECTION, A CRACK WAS NOTED IN THE LIFT LINK FITTING. TRANSMISSION WAS REMOVED AND SENT FOR REPAIR. THE TSO FOR THE COMPLETE TRANSMISSION WAS AT 785.1 AND TT 19803.1. NO AVAILABLE INFORMATION FOR TT ON THE SUMP ASSY CASE. (TC NR 20071127011)Nov 5, 2007 · Bell 205A1 · Main Rotor GearboxSDR CA070724005Control Lever · broken(CAN) THIS IS THE INITIAL REPORT. INFORMATION NOT HERE YET. THE PILOT COULD ONLY GET 92 PERCENT NR RP, LANDED THE AIRCRAFT NO INCIDENT, AFTER SHUTDOWN THE ENGINEER OPENED THE GOVERNOR SIDE ENGINE COWLING AND FOUND THE THE GOVERNOR LEVER BROKEN BOTH ENDS OF THEJul 23, 2007 · Bell 205A1 · Turbine GovernorSDR CA070807005Connector · burned(CAN) TRAINING FLIGHT, NOTICED SMOKE COMING UP FROM CENTER CONSOLE BEHIND VHF NR 2 RADIO. PUT DOWN, A/C ON GROUND. CO-PILOT JUMPED OUT TO CHECK IN BATT COMPARTMENT. NO ANOMALIES FOUND. FORCE TRIM CB POPPED. CARGO RELEASE LIGHT CAME ON AND STAYED ON. VHF RADIJul 17, 2007 · Bell 205A1 · Communications System WiringSDR CA070524001Pump · failed(CAN) DURING HELI-PORTABLE SEISMIC DRILLING OPERATIONS, UPON DESCENT WITH AN EXTERNAL LOAD: THE MASTER CAUTION WARNING INDICATION WAS ILLUMINATED. THE LOAD WAS SET AND RELEASED. THE CAUTION PANEL OBSERVED TO REVEAL THAT THE ENGINE DRIVEN FUEL PUMP WARNING LIGMay 17, 2007 · Bell 205A1 · Engine Fuel PumpSDR CA070412004Governor · damaged(CAN) DURING THE DAILY INSPECTION PERFORMED BY THE ENGINEER, THE SCREW HOLDING THE GOV SERVO LEVER PLATE IN PLACE WAS ENTIRELY BACKED OUT OF THE HOLE. THIS PART HAD BEEN REPLACED, TESTED AND ADJUSTED AT TSN 2346.3 FOR LOOSE SCREWS. THE SCREWS ARE STAKED IN PMar 30, 2007 · Bell 205A1 · Turbine GovernorSDR CA070418003Mount · cracked(CAN) ENGINE MOUNT WAS INSTALLED NEW IAW STC SH99-11. POWER PLANT WAS ALIGNED IAW MM SUPPLEMENT. THE MM SUPPLEMENT INCLUDES AN INSP EVERY 100 HRS OR ANNUALLY. NOTE TO INSPECT ENGINE MOUNTS FOR CRACKS, DAMAGE, CORROSION AND SECURITY. THE CRACK STARTED BELOW THMar 21, 2007 · Bell 205A1 · Engine Mount SectionSDR CA061222004Nut · cracked(CAN) THE ACORN NUTS WERE SENT OUT FOR NDT IAW THE REQUIREMENT OF THE OVERHAUL OF THE M/R HEAD ASSY. THE NDT SHOP FOUND A CRACK DEVELOPING NEAR THE BASE IN THE TRANSITION AREA OR CURL OF THE DOME AND THE GEAR PART OF THE ACORN NUTS. THE ESTIMATED TIME ON THEDec 4, 2006 · Bell 205B · Main Rotor HeadSDR CA060907005Actuator · failed(CAN) DURING LONG LINE SLINGING OPERATIONS, UPON APPROACHING A DROP ZONE WITH A LOAD. THE COLLECTIVE WAS RAISED TO CUSHION LANDING OF THE LOAD, THEN LOWERED TO TAKE TENSION OFF OF THE LINE. THE HELICOPTER TURNED TO THE LT AND THE RT TAIL ROTOR PEDAL WAS FOUND Aug 30, 2006 · Bell 205A1 · Rotorcraft Servo SystemSDR CA060727001Nut · cracked(CAN) THIS IS AN ON CONDITION ITEM. SO HISTORY MAY NOT BE ACCURATE. M/R HUB ASSY HAS 18437.6 TIME SINCE NEW. M/R HEAD ASSY WAS IN FOR O/H AND REQUIRES ACORN NUTS TO BE NDT. THIS ONE WAS FOUND CRACKED. (TC NR 20060727001)Jul 27, 2006 · Bell 205A1 · Main Rotor HeadSDR CA060602004Drag Brace · cracked(CAN) THE DRAG BRACE WAS IN THE COMPONENT SHOP GETTING ITS 1200 HR INSPECTION/24 MONTH INSPECTION. THE DRAG BRACE ASSEMBLY WAS PREPARED FOR NDT MAGNETIC PARTICLE INSPECTION. THE NDT SHOP FOUND THIS FITTING WAS CRACKED ON THE IB CURVE. (TC NR 20060602004)May 29, 2006 · Bell 205A1 · Main Rotor HeadSDR CA060524001Fitting · crackedAIRCRAFT WAS ON SEISMIC DRILL MOVE JOB. THE ENGINEER WAS DOING HIS DAILY INSPECTION WHEN NOTICED THAT ONE EAR OF THE LIFT LINK FITTING WAS APPEARED CRACKED. A CLOSER VISUAL LOOK CONFIRMED IT WAS CRACKED. INVESTIGATING IF THE BUSHING WAS WRONG FOR THIS INSTMay 19, 2006 · Bell 205A1 · Main Rotor GearboxSDR CA060331005Saddle · crackedCRACK WAS FOUND ON SKID TUBE AT FORWARD CROSSTUBE MOUNTING SADDLE. THERE WAS NO REPORT OF A HARD LANDING WITH THIS AIRCRAFT AT THIS TIME. TIMES FOR THESE SKID TUBES WERE NOT AVAILABLE.Mar 27, 2006 · Bell 205A1 · Wheel/Ski/FloatSDR CA050816005Mount · cracked(CAN) THE ENGINE MOUNT WAS MODIFIED BY STC SH99-11 WHICH ALLOWS THE MOUNT TO BECOME ADJUSTABLE. THE ADJUSTABLE PORTION OF THE MOUNT IS RIVETED TO ONE LEG AND IT CRACKED FROM ONE OF RIVET HOLES SECURING THE ADJUSTABLE TURN BARREL TO THE MOUNT LEG.Aug 12, 2005 · Bell 205A1 · Engine Mount SectionSDR CA050816006Mount · cracked(CAN) THE ENGINE MOUNT WAS MODIFIED BY STC SH99-11 WHICH ALLOWS THE MOUNT TO BECOME ADJUSTABLE. THE ADJUSTABLE PORTION OF THE MOUNT IS RIVETED TO ONE LEG AND IT CRACKED FROM ONE OF RIVET HOLES SECURING THE ADJUSTABLE TURNBARREL TO THE MOUNT LEG.Aug 12, 2005 · Bell 205A1 · Engine Mount SectionSDR CA050707005Hub · worn(CAN) DURING LAG PIN REPLACEMENT BLADE WAS REMOVED. UPON REMOVAL OF BLADE HUB WAS INSPECTED AND THE PROBLEM WAS FOUND. THE UPPER SURFACE OF THE LOWER HUB HALF KRON BEARING SURFACE WAS WORN THROUGH TO METAL IN APPROXIMATELY 1/5 OF ITS CIRCUMFERENCE. NO INSPEJun 24, 2005 · Kaman K1200 · Main Rotor HeadSDR CA051115006Structure · crackedON MAINTENANCE SHUTDOWN DURING A NORMAL HELI LOGGING DAY, DURING INSP OF FLIGHT CONTROLS THE APPRENTICE NOTICED SOME SMOKING COMING FROM THE BOTTOM CORNER OF THE STBD OCTAGONAL CARGO DOOR. UPON FURTHER INSP IT WAS DETERMINED TO BE A CRACK.Jul 5, 2004 · Kaman K1200 · Cargo/Baggage DoorsSDR 2004FA0000423Pin · unserviceableTHE LEADING EDGE OF THE LT SIDE TEETER PIN WAS DAMAGED (MUSHROOMED). FURTHER INSPECTION SHOWED THAT THE HEAD SIDE OF THE INSIDE DIAMETER OF THE LINER THAT THE TEETER PIN SITS IN IS ALSO DAMAGED. THE LINER IS DEFORMED AND PROTRUDES IN AN IRREGULAR MANNER ON TMar 25, 2004 · N358KA · Kaman K1200 · Main Rotor HeadSDR CA040127014Pump · failed(CAN) WHILE HELICOPTER WAS CONDUCTING AERIAL LIFT WORK THE PILOT NOTED THE ENGINE FUEL PUMP LIGHT CAME ON. HE RETURNED TO THE STAGING AREA AND LANDED UNEVENTFULLY. THROUGH TROUBLESHOOTING ON THE GROUND IT WAS DISCOVERED THAT ONE ELEMENT OF A DUAL ELEMENT PUMPDec 28, 2003 · Bell 205A1 · Fuel Control/Reciprocating EnginesSDR CA040128006Pump · worn(CAN) FUEL CONTROL P/N 1-170-240-93, S/N 5ADS1907 WAS RECEIVED DUE TO DAMAGED MAIN DRIVE SHAFT SPLINE. DISASSEMBLED AND INSPECTED FCU AND FOUND DAMAGED PUMP ASSEMBLY. RECORD OF INSPECTION IAW SB73-39. FCU S 91 AND 93 HAVE TIP SEAL PUMP, AND THEY CAN BE INSDec 28, 2003 · Bell 205A1 · Fuel Control/Reciprocating EnginesSDR AUS20031090Compressor · unserviceable(AUS) ENGINE COMPRESSOR SECTION CONTAINED COMPONENTS FROM AN ENGINE INVOLVED IN AN AIRCRAFT CRASH. ENGINE HAD BEEN ASSEMBLED FROM COMPONENTS FROM FIVE DIFFERENT ENGINES. NO HISTORY CARDS WERE SUPPLIED FOR THE COMPRESSOR MODULE BUT INVESTIGATION FOUND THAT THE Oct 10, 2003 · Turbine Engine Compressor SectionSDR CA040204006Fuel Control · failed(CAN) ENGINE STOPPED IN-FLIGHT.Sep 11, 2003 · Bell 205A1 · Fuel Controlling SystemSDR FZO2003F00000Drive Shaft · chafedPILOT FELT HARMONIC VIBRATION DURING REDUCE POWER DECENT INTO DIP SITE. FOUND T/R DRIVE SHAFT PN 204-040-623-011 RUBBING ON 205-060-923-001 BOOT ASSY. BOOT SEAL ECE-300-3/3 OIL SOAKED AND DEBONDED FROM BOOT LETTING BOOT SIDE. DOWN AND AMAKING CONTACT WITH TJul 18, 2003 · N6288Y · Bell 205A1 · Tail Rotor Drive Shaft
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