# Service difficulty reports: Lycoming T5311B A list on [Lycoming T5311B](https://openairdocs.org/engine/lycoming-t5311b.md). Newest first. General aviation reporting is voluntary. - [SDR CA190806009](https://openairdocs.org/sdr/CA190806009.md): Bolt · broken · Jul 31, 2019 · Bell 204B · Rotorcraft Tail Boom > (CAN) DURING CRUISE FLIGHT THE PILOT HEARD "WHAT SOUNDED LIKE A SMALL BANG, A SOUND THAT IN THE PAST I HAD BEEN A METAL DRINK BOTTLE OR CELLPHONE DROPPING ONTO THE FLOOR." THE PILOT REDUCED POWER/AIRSPEED AND CHECKED THE GAUGES - NO VIBRATIONS OR ABNORMALITIES - [SDR CA130820004](https://openairdocs.org/sdr/CA130820004.md): Bolt · sheared · Aug 15, 2013 · Bell 204B · Tail Rotor Head > (CAN) DURING CRUISE FLIGHT, THE ACFT DEVELOPED A SUDDEN AND SEVERE VIBRATION. THE PILOT IMMEDIATELY LANDED AND SHUTDOWN. INSPECTION OF THE ACFT SHOWED THE INBD BOLT SECURING TAIL ROTOR PITCH LINK TO THE TAIL ROTOR GRIP HAD SHEARED AND THE TAIL ROTOR BLADES H - [SDR CA130326007](https://openairdocs.org/sdr/CA130326007.md): Nut · damaged · Mar 26, 2013 · Bell 204B · Tail Rotor Drive Shaft > (CAN) DURING SCHEDULED MAINTENANCE OF TAIL ROTOR DRIVESHAFT, NEW BOLTS AND NUTS BEING INSTALLED, A NEW NUT WAS FOUND TO HAVE NO SELF LOCKING ABILITY ON ANY BOLT NEW OR OLD. SUSPECT MFG DEFECT. - [SDR CA110516029](https://openairdocs.org/sdr/CA110516029.md): Panel · delaminated · May 16, 2011 · Bell 204B · Fuselage Main, Plate/Skin > DURING A VISUAL INSPECTION OF THE ABOVE NOTED ACFT THE CENTER ROOF SECTION WAS FOUND SEVERLY DELAMINATED. THE ROOF PANEL WAS REMOVED AND THE AREA FUTHER INSPECTED FOR DEFECTS. NONE NOTED. - [SDR CA110516030](https://openairdocs.org/sdr/CA110516030.md): Panel · delaminated · May 16, 2011 · Bell 204B · Fuselage Miscellaneous Structure > DURING A VISUAL INSPECTION OF THE ACFT THE ENGINE DECK WAS FOUND TO BE DELAMINATED AND THE HONEYCOMB WAS FOUND TO BE SOFT IN THE ENTIRE PANEL. PANEL WAS REMOVED AND OVERHAULED. - [SDR CA110204009](https://openairdocs.org/sdr/CA110204009.md): Volt Regulator · failed · Jan 31, 2011 · Bell 204B · DC Regulator > DURING CRUISE FLIGHT THE PILOT NOTICED THE AMMETER FLUCTUATE AND THE GENERATOR LIGHT FLICKER. THE PILOT BEGAN TO DESCEND WHEN THE GENERATOR LIGHT, LT BOOST PUMP LIGHT AND ROTOR RPM AUDIO ALL CAME ON AND THE COCKPIT BEGAN TO FILL WITH SMOKE. ALL UNNECESSARY SWI - [SDR CA090512011](https://openairdocs.org/sdr/CA090512011.md): Bulkhead · cracked · May 8, 2009 · Bell 204B · Rotorcraft Tail Boom > (CAN) DURING A VISUAL INSP, A CRACK WAS FOUND AT THE BOTTOM OF THE RT ANGLE AT TAILBOOM TO FUSELAGE JUNCTION (PN 204-030-713-101). AFTER REMOVAL OF THE TAILBOOM AND SHIM PADS THE TAILBOOM ATTACHMENT BULKHEAD WAS FOUND CRACKED AT 3 OF THE 4 ATTACHMENT POINTS. ( - [SDR CA081017008](https://openairdocs.org/sdr/CA081017008.md): Longeron · cracked · Oct 3, 2008 · Bell 204B · Rotorcraft Tail Boom > (CAN) DURING A VISUAL INSPECTION OF THE ACFT THE AME NOTICED A CRACK IN THE UPPER LT TAILBOOM LONGERON APROX. 3 INCHES AFT OF THE TAILBOOM ATTACHMENT FITTING. ACFT GROUNDED FOR REPAIRS. - [SDR CA071010005](https://openairdocs.org/sdr/CA071010005.md): Blade · cracked · Aug 28, 2007 · Bell 204B · Main Rotor Blades > (CAN) ON TUESDAY THE 28TH OF AUGUST 2007, AT APPROX 19:00, LANDED AT THE STAGING AREA. THE PILOT COMMENTED THAT THERE WAS A VIOLENT LATERAL VIBRATION. AT THIS TIME THE TRANSMISSION WAS OBSERVED SHAKING EXCESSIVELY AND IT WAS DECIDED TO SHUT THE AIRCRAFT DOWN W - [SDR CA070122011](https://openairdocs.org/sdr/CA070122011.md): Collective Stick · ratcheting · Jan 22, 2007 · Bell 204B · Main Rotor Control > (CAN) PILOT COMPLAINED OF RATCHETING FEEL TO COLLECTIVE CONTROL STICK. AIRCRAFT RETURNED TO BASE. INSPECTION REVEALED THAT THE COLLECTIVE FRICTION SURFACE ROLL PIN WAS WORKING INTERNALLY AND CAUSING THE RATCHETING FEEL. ELBOW WAS REPLACED. (TC NR 2007012201 - [SDR CA060818004](https://openairdocs.org/sdr/CA060818004.md): Bolt · loose · Aug 14, 2006 · Bell 204B · Tail Rotor Control System > (CAN) DURING A 100 HOUR INSPECTION THE ENGINEER NOTED A LARGE AMOUNT OF PLAY IN THE CLEVIS OF THE TAIL ROTOR FLIGHT CONTROL ROD. INVESTIGATION REVEALED AN UNDERSIZED BOLT, IE SMALLER DIAMETER, WAS INSTALLED. THE CORREECT BOLT, P/N AN175-20 WAS INSTALLED AN - [SDR CA050715002](https://openairdocs.org/sdr/CA050715002.md): Turnbuckle · unsecure · Jul 10, 2005 · Bell 204B · Tail Rotor Head > LOCKWIRE LEFT UNLOCKWIRED RESULTING IN TURNBARREL BECOMING UNDONE RESULTING IN TAILROTOR PITCH CHANGE FAILURE. SPEED RIGS WERE LOCK WIRED ON THE ONE END BUT THE ENGINEER DIDN'T RECOGNIZE THE OTHER END REQUIRED LOCKWIRE. - [SDR CA050418007](https://openairdocs.org/sdr/CA050418007.md): Relay · defective · Apr 11, 2005 · Bell 204B · DC Generating System > ON SHUTDOWN ENGINE CONTINUED TO MOTOR OVER SLOWLY. CONTACTS STUCK. RCR REPLACED AND PROBLEM SOLVED. - [SDR CA050418008](https://openairdocs.org/sdr/CA050418008.md): Nut · cracked · Apr 8, 2005 · Bell 204B · Engine Controls > UPON INSP NOTICED CRACKED JAN NUT ON LINEAR ACTUATOR. - [SDR CA050418006](https://openairdocs.org/sdr/CA050418006.md): Housing · worn · Apr 4, 2005 · Bell 204B · Tail Rotor Head > (CAN) DURING INSPECTION THE TAIL ROTOR CONTROL WAS REMOVED AND INSPECTED FOR WEAR. WEAR WAS FOUND BEYOND LIMITS IN THE HOUSING. THIS ITEM IS A 1000 HOUR OVERHAUL INTERVAL. - [SDR CA050427008](https://openairdocs.org/sdr/CA050427008.md): Blade · damaged · Apr 1, 2005 · Bell 204B · Main Rotor Blades > VOID, CHORDWISE STATION 155 TO 157, HALF INCH WIDE THREE INCHES LONG. BELL HELICOPTER VERDICT THAT BLADE STILL SERVICEABLE. BHT ALLOWS VOID IN THIS AREA. 6 INCHES SPANWISE BY THE FULL CHORDWISE WIDTH OF CORE. BLADE RETURNED TO SERVICE. WILL CONTINUE TO MO - [SDR CA030923010](https://openairdocs.org/sdr/CA030923010.md): Yoke · cracked · Sep 12, 2003 · Bell 204B · Tail Rotor Head > (CAN) TAIL ROTOR HUB ASSY WAS SENT FOR OVERHAUL. YOKE WAS SENT FOR NDT AS PART OF O/H AND WAS FOUND TO BE CRACKED. - [SDR CA040301002](https://openairdocs.org/sdr/CA040301002.md): Compressor · failed · Aug 17, 2003 · Bell 204B · Turbine Engine Compressor Section > (CAN) THE AIRCRAFT DEPARTED A STAGING AREA, SHORTLY AFTER TAKEOFF, THE AIRCRAFT HAD AN ENGINE FAILURE AND CRASHED IN TALL TREES. THE PILOT WAS THE ONLY OCCUPANT AND WAS KILLED ON IMPACT. THE ENGINE WAS RECEIVED FROM OVERHAUL AND INSTALLED 18 HOURS PRIOR TO THE - [SDR CA030610011](https://openairdocs.org/sdr/CA030610011.md): Spar · cracked · Jun 7, 2003 · Bell 204B · Rotorcraft Tail Boom > (CAN) ENGINEER OPENED TAIL ROTOR DRIVESHAFT COVER TO CHANGE COUPLINGS AND FOUND A CRACK HAD DEVELOPED IN THE VERTICAL FIN SPAR. STARTING AT THE TOP LIGHTENING HOLE AND GOING LT TO THE OUTER EDGE OF THE SPARE. OUTER LT SKIN WAS ALSO CRACKED APPROX. SIX INCHES. - [SDR CA030317016](https://openairdocs.org/sdr/CA030317016.md): Nut · cracked · Mar 14, 2003 · Bell 204B · Tail Rotor Head > (CAN) ON VISUAL INSPECTION NUT WAS FOUND TO BE CRACKED AT WORM GEAR THREAD. THESE PARTS HAVE A 1000 HR NDT INSPECTION. THIS COMPANY INCLUDE A 300 HR VISUAL THIS WAS FOUND DURING THE VISUAL. - [SDR CA030421004](https://openairdocs.org/sdr/CA030421004.md): Longeron · cracked · Jan 31, 2003 · Bell 204B · Rotorcraft Tail Boom > (CAN) UPPER LT ATTACH LONGERON CRACKED AFT OF HOT BONDED DOUBLER. CRACK APPEARS TO HAVE STARTED AT A RIVET HOLE. THE CRACK WAS DISCOVERED DURING A ENGINE REMOVAL WHERE THE AFT ENGINE COWL WAS REMOVED EXPOSING THE LONGERON. THE CRACK MEASURES APPROX 3 INCHES - [SDR CA030421005](https://openairdocs.org/sdr/CA030421005.md): Longeron · cracked · Jan 31, 2003 · Bell 204B · Fuselage Main, Longeron/Stringer > (CAN) MODIFICATION OF THE DOOR ASSEMBLY WAS COMPLETED PRIOR IAW BHT. TB204-79-11. THE CRACKED PIECES WERE REPLACED WITH NEW PIECES AND REINSTALLED IAW TB 204-79-11. - [SDR CA021105012](https://openairdocs.org/sdr/CA021105012.md): Bellcrank · cracked · Nov 4, 2002 · Bell 204B · Main Rotor Control > (CAN) AT 1000 HR INSPECTION BELLCRANK FOR THE CYCLIC WAS REMOVED FOT GREASING OF THE BEARINGS. BELLCRANK WAS FOUND TO BE CRACKED AT ONE BEARING. CRACK WAS COMPLETELY THROUGH TO THE OUTER RACE OF THE BEARING. BELLCRANK WAS REPLACED WITH A SERVICEABLE ONE.ALL OT - [SDR CA011109007](https://openairdocs.org/sdr/CA011109007.md): Segment · missing · Oct 24, 2001 · Bell 204B · Tail Rotor Gearbox > (CAN) UPON INSTALLATION OF THE NEW CHAIN, THE ENGINEER NOTICED A SPACE BETWEEN SOME CHAIN LINKS. CHAIN IS MISSING A SEGMENT. - [SDR CA000801011](https://openairdocs.org/sdr/CA000801011.md): Case · cracked · Jul 22, 2000 · Bell 204B · Main Rotor Gearbox > (CAN) WHILE CARRYING OUT A DAILY INSPECTION, THE AME NOTICED A CRACK ON THE TRANSMISSION SUPPORT CASE WHERE THE LIFT LINK ATTACHES. - [SDR AU000186](https://openairdocs.org/sdr/AU000186.md): Blade · failed · Jan 25, 2000 · Bell UH1B · Turbine Engine Compressor Section > (AUS) THIRD STAGE COMPRESSOR DISC AND BLADES DESTROYED. DOWNSTREAM COMPRESSOR DAMAGE. NO DAMAGE TO THE FIRST TWO STAGES. - [SDR CA991027081](https://openairdocs.org/sdr/CA991027081.md): Floorbeam · cracked · Sep 15, 1999 · Bell 204B · Fuselage Main, Floor Beam > (CAN) DURING REMOVAL OF FLOORBOARDS DURING SCHEDULED MAINTENANCE, THE LEFT MAIN BEAM WEB WAS FOUND CRACKED. REPAIR CARRIED OUT IAW BELL DATA. SUBMITTER SUSPECTED CRACK WAS CAUSED DUE TO HEAVY INTERNAL CARGO. - [SDR CA990719005](https://openairdocs.org/sdr/CA990719005.md): Housing · worn · Jun 30, 1999 · Bell 204B · Tail Rotor Control System > (CAN) PILOT NOTICED BALL WAS OUT OF TURN/SLIP INDICATOR SO THEN PILOT INPUTTED THE RIGHT PEDAL TO CORRECT. HOWEVER, THE ROTORCRAFT DID NOT RESPOND TO RIGHT PEDAL INPUT, BUT DID RESPOND TO LEFT PEDAL INPUT. PILOT THEN LANDED THE ROTORCRAFT. SUBSEQUENT INVEST - [SDR CA990728048](https://openairdocs.org/sdr/CA990728048.md): Bearing · wrong part · Jun 29, 1999 · Bell 204B · Starter-Generator > (CAN) UNIT SENT TO O/H. WHEN SG WAS DISASSEMBLED, IT WAS NOTED THAT THE WRONG BEARINGS WERE INSTALLED (NOT THE MANUFACTURER'S BEARINGS). UNAPPROVED PARTS REPLACED AND RETURNED TO SERVICE. - [SDR CA990119011](https://openairdocs.org/sdr/CA990119011.md): Cross Tube · cracked · Dec 29, 1998 · Bell 204B · Main Landing Gear Strut/Axle/Truck > (CAN) CROSS TUBE SHEARED ON LANDING CAUSING DAMAGE TO FUSE AND TAIL BOOM. CRACK IS BELIEVED TO HAVE STARTED AT AN INTERNAL CORROSION PIT OR VOID. - [SDR CA981109011](https://openairdocs.org/sdr/CA981109011.md): Dampener · cracked · Oct 27, 1998 · Bell 204B · Starter-Generator > (CAN) STARTER/GENERATOR IN SHOP FOR REPAIR WAS FOUND TO HAVE WRONG DAMPENER BACKPLATE INSTALLED CAUSING INSUFFICIENT SPRING PRELOAD WHICH RESULTED IN EXCESS WEAR ON THE SPLINED HUB, DAMPENER PLATE, AND SHAFT SPLINE. - [SDR CA990412006](https://openairdocs.org/sdr/CA990412006.md): Mount · worn · Oct 20, 1998 · Bell 204B · Engine Mount Section > (CAN) DURING INSPECTION, GRAY PASTE WAS NOTED UNDER THE SERVICE DECK OF THE ENGINE MOUNTS. REMOVAL OF THE ENGINE AND DECK DISCLOSED THE CRACKED BEAM CAP. THE ENGINE WAS ABLE TO ROCK ON THE BEAM CAPS WHEN TORQUE WAS APPLIED. LEFT AND RIGHT BEAM CAPS AND ALL - [SDR CA980519006](https://openairdocs.org/sdr/CA980519006.md): Valve · broken · May 8, 1998 · Bell 204B · Hydraulic System, Main > (CAN) ON RUN-UP, UNABLE TO SWITCH HYDRAULICS TO MANUAL. HYDRAULIC BYPASS VALVE CANNON PLUG RECEPTACLE BROKEN OFF AT ITS BASE. INTERIOR CONNECTIONS BROKEN ALLOWING INTERMITTENT CONTACT. - [SDR CA971223001](https://openairdocs.org/sdr/CA971223001.md): Cap Angle · broken · Dec 11, 1997 · Bell 204B · Fuselage Fixed Partitions > (CAN) UPPER CAP ANGLE FOUND BROKEN AND A CRACK HAD DEVELOPED IN THE MAIN PANEL. CRACK APPROX 2 INCHES TO 2.50 INCHES IN FRONT OF P/N 204-060-651-001, TUBE ASSY AND EXTENDING 10 INCHES VERTICAL DOWN AND DISAPPEARS BEHIND THE OWER CAP ANGLE. THE CRACK ALSO E - [SDR CA960814201](https://openairdocs.org/sdr/CA960814201.md): Inner Ring · cracked · Aug 4, 1996 · Bell 204B · Main Rotor Mast/Swashplate > (CAN) ON DAILY INSPECTION, CRACK FOUND IN L.H. TRUNNION MOUNTING EAR OF THE SWASHPLATE INNER RING. ## 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 = 'T5311B' ORDER BY difficulty_date DESC ``` This list as a web page: https://openairdocs.org/engine/lycoming-t5311b/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.