# Service difficulty reports: Lycoming T5508D A list on [Lycoming T5508D](https://openairdocs.org/engine/lycoming-t5508d.md). Newest first. General aviation reporting is voluntary. - [SDR CA130715017](https://openairdocs.org/sdr/CA130715017.md): Fcu · malfunctioned · Jul 13, 2013 · Bell 214B1 · Fuel Control/Turbine Engines > (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 S - [SDR CA120504004](https://openairdocs.org/sdr/CA120504004.md): Turbine Wheel · damaged · May 1, 2012 · Bell 214B · Turbine Section > (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 APPROVAL - [SDR CA130610012](https://openairdocs.org/sdr/CA130610012.md): Barrel · cracked · Jul 20, 2011 · Bell 214B1 · Rotorcraft Servo System > (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 LEAKAGE - [SDR CA100903013](https://openairdocs.org/sdr/CA100903013.md): Turbine Nozzle · cracked · Apr 16, 2010 · Bell 214B1 · Turbine Section > DURING 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 - [SDR CA101230002](https://openairdocs.org/sdr/CA101230002.md): Fuel Control · malfunctioned · Sep 13, 2009 · Fuel Control/Turbine Engines > (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 BE - [SDR CA090430003](https://openairdocs.org/sdr/CA090430003.md): Spindle · mismanufactured · Apr 17, 2009 · Bell 214B1 · Main Rotor Head > (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 F - [SDR CA081017006](https://openairdocs.org/sdr/CA081017006.md): Horn · cracked · Sep 25, 2008 · Bell 214B1 · Rotorcraft Tail Boom > (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. - [SDR CA080404003](https://openairdocs.org/sdr/CA080404003.md): Liner · sheared · Aug 7, 2007 · Bell 214B1 · Accessory Gearboxes > (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 WITH - [SDR CA060627003](https://openairdocs.org/sdr/CA060627003.md): Spindle · broken · Jun 25, 2006 · Bell 214B1 · Main Rotor Head > (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 TH - [SDR CA060524008](https://openairdocs.org/sdr/CA060524008.md): Spindle · broken · May 24, 2006 · Bell 214B · Main Rotor Gearbox > DONT 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 AND - [SDR CA060209004](https://openairdocs.org/sdr/CA060209004.md): Horn · cracked · Feb 6, 2006 · Bell 214B1 · Elevator Miscellaneous Structure > (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 CHAN - [SDR CA041228002](https://openairdocs.org/sdr/CA041228002.md): Housing · stripped · Dec 5, 2004 · Bell 214B1 · Turbine Engine Compressor Section > (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 CASTING - [SDR CA040531005](https://openairdocs.org/sdr/CA040531005.md): Support · worn · Dec 3, 2003 · Bell 214B1 · Main Rotor Mast/Swashplate > DURING 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, C - [SDR CA021108017](https://openairdocs.org/sdr/CA021108017.md): Wire · chafed · May 28, 2002 · Bell 214B · Electrical Power System Wiring > (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 WI - [SDR CA010724008](https://openairdocs.org/sdr/CA010724008.md): Liner · unserviceable · Jul 5, 2001 · Bell 214B1 · Turbine Engine Reduction Gear > (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 TO - [SDR CA000925006](https://openairdocs.org/sdr/CA000925006.md): Fuel Control · worn · Aug 9, 2000 · Bell 214B1 · Fuel Control/Turbine Engines > (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 - [SDR CA010921003](https://openairdocs.org/sdr/CA010921003.md): Hose · deteriorated · Sep 26, 1999 · Bell 214B · Hydraulic System, Main > (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. - [SDR CA000110005](https://openairdocs.org/sdr/CA000110005.md): Spur Gear · broken · Sep 24, 1999 · Bell 214B1 · Turbine Engine Reduction Gear > (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. - [SDR CA990513001](https://openairdocs.org/sdr/CA990513001.md): Servo · defective · Apr 28, 1999 · Bell 214B1 · Hydraulic System, Main > (CAN) MAIN HYDRAULIC SERVO'S RETURNED FROM REPAIR FACILITY. MANY DEFECTS WERE NOTED WHICH AFFECT AIRWORTHINESS. SERVO'S REPAIRED AND RETURNED TO SERVICEABLE STATUS. ## The whole list in SQL Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS: ```sql 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 ``` This list as a web page: https://openairdocs.org/engine/lycoming-t5508d/reports --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.