Lycoming T5508D

Service difficulty reports · 19

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 = 'T5508D'
  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 CA130715017Fcu · malfunctioned(CAN) PART WAS RECEIVED AS AN O/H UNIT AND INSTALLED. ABILITY TO MAINTAIN DESIRED RPM WITHIN LIMITS DEGRADED QUICKLY. FINAL TEST FLIGHTS HAD MINOR SURGING AND HUNTING NOTED. ON REMOVAL, NOTED FUEL LEAKS IN THE DRIVE SPLINE, 2 SEALS, WASHING OUT THE GREASE SJul 13, 2013 · Bell 214B1 · Fuel Control/Turbine EnginesSDR CA120504004Turbine Wheel · damaged(CAN) OPERATOR IS IMPROPERLY MARKING PARTS THAT THEY MFG, PURSUANT TO A LICENSING AGREEMENT WITH OEM MFG. REF: MFG AO 230-91 IAW CHAPTER 561 AERONAUTICAL PRODUCTS. PARTS ARE BEING PRODUCED WITH NO MFG CAGE CODE, "HAS ONLY THE OEM MFG CAGE CODE DESIGN APPROVALMay 1, 2012 · Bell 214B · Turbine SectionSDR CA130610012Barrel · cracked(CAN) MAIN ROTOR ACTUATOR, SERVO, FOUND TO HAVE INCREASING LEAKAGE DURING DAILY INSPECTIONS OVER A PERIOD OF 3 OPS DAYS UNTIL IT WAS REMOVED FOR EXCESSIVE LEAKAGE. UNIT LATER SENT FOR REPAIR AND FOUND TO HAVE CRACKED BARREL, PN 41005043 THAT CAUSED THE LEAKAGEJul 20, 2011 · Bell 214B1 · Rotorcraft Servo SystemSDR CA100903013Turbine Nozzle · crackedDURING AN ENGINE "HOT-SECTION INSP" A SUBSTANTIAL CRACK WAS DISCOVERED IN THE 2ND TURBINE NOZZLE ASSY, THE CRACK IS LOCATED AT THE JOINT FORMED BY THE RING ASSY AND OUTER SHROUD. THIS CIRCUMFERENTIAL CRACK IS APPROX (6) INCHES IN LENGTH. FURTHER ANALYTICAL Apr 16, 2010 · Bell 214B1 · Turbine SectionSDR CA101230002Fuel Control · malfunctioned(CAN) WHILE HOVERING IN FIRE SUPPRESSION ACTIVITY, THE PILOT REPORTED A COMPRESSOR STALL/SURGE FOLLOWED BY POWER LOSS FORCING AN UNSCHEDULED LANDING. SUBSEQUENT INVESTIGATION REVEALED POWER TURBINE FAILURE. CONTRIBUTING FACTORS TO THE STALL/SURGE MAY HAVE BESep 13, 2009 · Fuel Control/Turbine EnginesSDR CA090430003Spindle · mismanufactured(CAN) ASB 214-08-70 NOW IN REVISION `C` RELATES TO IMPOSING A LIMIT LIFE ON SPINDLE ASSY 214-030-606-005. WHEN THE ORIGINAL ASB 214-08-70 CAME OUT. THE NEW MFG SPINDLES WHERE SUPPLIED AT THE SAME TIME. THE HOLE PATTERN WAS NOT CORRECT AND THE PIECE WOULD NOT FApr 17, 2009 · Bell 214B1 · Main Rotor HeadSDR CA081017006Horn · cracked(CAN) BOTH `EARS` (LT & RT) OF THE HORN TO WHICH THE ELEVATORS ATTACH CRACKED. COMMON PROBLEM WITH THESE HELICOPTERS. SENT A PREVIOUSLY CRACKED HORN TO BELL HELICOPTER FOR ENGINEERING ANALYSIS, BUT HAVE NOT HEARD ANY RESULTS YET.Sep 25, 2008 · Bell 214B1 · Rotorcraft Tail BoomSDR CA080404003Liner · sheared(CAN) DURING THE COURSE OF A 100 HR INSP, AME FOUND A LARGE AMOUNT OF NON-FERROUS METAL PARTICLES IN THE REDUCTION GEARBOX OIL FILTER AND THE OIL DRAINED FROM THE GEARBOX. CHIP PLUG WAS INSPECTED AND FOUND CLEAN. REDUCTION GEARBOX WAS REMOVED AND REPLACED WITHAug 7, 2007 · Bell 214B1 · Accessory GearboxesSDR CA060627003Spindle · broken(CAN) TRANSMISSION SPINDLE ASSY P/N 214-040-606-005 S/N A12-01304 BROKE IN HALF DURRING FLIGHT, AND THE PILOT HEARD A LOUD BANG AND BEGAN A EMERGENCY LANDING. APON SUCSESSFULL LANDING THE ENGINEER FOUND THE SPINDLE CRACKED IN HALF. DURRING THE SHORT TIME IN THJun 25, 2006 · Bell 214B1 · Main Rotor HeadSDR CA060524008Spindle · brokenDONT HAVE ANY OTHER INFO AT THIS TIME, AS THIS INCIDENT JUST OCCURRED THIS MORNING. WILL ADD INFORMATION AS IT COMES IN. THIS INCIDENT SEEMS VERY SIMILAR TO ONE 16 OCT 1996 NTSB REPORT NUMBER A96P0231. WITH ONE GOOD DIFFERENCE, NO LOSS IN FLIGHT CONTROL ANDMay 24, 2006 · Bell 214B · Main Rotor GearboxSDR CA060209004Horn · cracked(CAN) AFTER LANDING AND SHUTDOWN, DURING REGULAR INSPECTION, A CRACK WAS FOUND IN THE ELEVATOR HORN ASSY. PART WAS REMOVED AND REPLACED BEFORE FURTHER FLIGHT. (UNDER CODES F1 WAS USED HOWEVER FLIGHT CONTROLS WERE NOT AFFECTED, AS PILOT DID NOT NOTICE ANY CHANFeb 6, 2006 · Bell 214B1 · Elevator Miscellaneous StructureSDR CA041228002Housing · stripped(CAN) DURING REFUELING BETWEEN HELI-LOGGING CYCLES AME ON SITE ROUTINELY OPENS ENGINE COWLS FOR AN INSPECTION OF ENGINE COMPARTMENT AREA. HE NOTICED AFT ENGINE MOUNT ROD END (BELL PN 214-060-114-001) HAD COMPLETELY PULLED OUT OF ENGINE COMPRESSOR HALF CASTINGDec 5, 2004 · Bell 214B1 · Turbine Engine Compressor SectionSDR CA040531005Support · wornDURING AN INSPECTION CHECK ON THE SWASH PLATE THE FRICTION WAS NOTED AS VERY TIGHT. UPON DISASSEMBLY, IT WAS FOUND THAT ONE OF THE FOUR BEARINGS RIDING ON THE SUPPORT HAD LOST IT'S 'COATING' ENTIRELY. THE RESULTING METAL/METAL CONTACT WORE INTO THE SUPPORT, CDec 3, 2003 · Bell 214B1 · Main Rotor Mast/SwashplateSDR CA021108017Wire · chafed(CAN) WHILE HOVERING DURING HELI-LOGGING OPERATIONS, PILOT NOTICED SMOKE AND SPARKS ORIGINATING FROM THE LT OVERHEAD CCT BREAKER PANEL. THE PILOT INITIATED AN UNSCHEDULED LANDING AND SHUT DOWN THE A/C WITHOUT FUTHER INCIDENT. IT WAS LATER DETERMINED THAT A WIMay 28, 2002 · Bell 214B · Electrical Power System WiringSDR CA010724008Liner · unserviceable(CAN) AFTER RECEIVING CHIP IND. FROM REDUCTION GEARBOX FILTER REMVD FOR INSP. OIL IN FILTER & BOWL FOUND TO BE BLACK WITH FERROUS MATERIAL PRESENT. REDUCTION GEARBOX THEN REMOVED & INIT INSP REVEALED THAT GEARBOX INPUT GEAR NUT P/N 214-040-236-001 HAD LOST TOJul 5, 2001 · Bell 214B1 · Turbine Engine Reduction GearSDR CA000925006Fuel Control · worn(CAN) PERIODIC ENGINE N2 DROOP WITH POWER APPLICATION WITH SLOW RECOVERY WAS REPORTED. DURING SUBSEQUENT TROUBLESHOOTING, N2 DROOPED WITH NO NR RECOVERY UNTIL COLLECTIVE WAS CYCLED SEVERAL TIMES. N2 LEVER ON FUEL CONTROL UNIT APPEARS TO BE ROUGH WHEN CYCLED Aug 9, 2000 · Bell 214B1 · Fuel Control/Turbine EnginesSDR CA010921003Hose · deteriorated(CAN) OIL SOAKED HOSE CLAMP CAUSED RUBBER TO DETERIORATE ON THE HOSE CLAMP WHICH CAUSED THE STEEL BRADING AROUND THE HOSE TO ERODE, THUS CAUSING THE HOSE TO LEAK.Sep 26, 1999 · Bell 214B · Hydraulic System, MainSDR CA000110005Spur Gear · broken(CAN) SPUR GEAR THAT DRIVES FCU FAILED. THIS WAS SPECIFIED TO BE A GEAR ALLIENMENT PROBLEM ORIGINATING AT MANUFACTURE. TSB NOTIFIED BY OPERATOR. BULLETIN EXPECTED TO FOLLOW FROM ALLIED TO HAVE RGB BORE ALIGNMENT CHECKED AT O/H.Sep 24, 1999 · Bell 214B1 · Turbine Engine Reduction GearSDR CA990513001Servo · defective(CAN) MAIN HYDRAULIC SERVO'S RETURNED FROM REPAIR FACILITY. MANY DEFECTS WERE NOTED WHICH AFFECT AIRWORTHINESS. SERVO'S REPAIRED AND RETURNED TO SERVICEABLE STATUS.Apr 28, 1999 · Bell 214B1 · Hydraulic System, Main
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