# Service difficulty reports: Lycoming T5313B

A list on [Lycoming T5313B](https://openairdocs.org/engine/lycoming-t5313b.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 3 · 147 reports

- [SDR CA130528009](https://openairdocs.org/sdr/CA130528009.md): Tube · cracked · May 27, 2013 · Bell 205A1 · Hydraulic System, Main
  > (CAN) CRACKED TUBE UNDERNEATH FITTING SLEEVE, TUBE POPPED OUT OF FITTING AND BLEW OUT MOST OF FLUID.
- [SDR CA130212025](https://openairdocs.org/sdr/CA130212025.md): Fuel Cell · leaking · Feb 12, 2013 · Bell 204B · Fuel Storage
  > (CAN) FUEL CELL FOUND WEEPING FROM MULTIPLE LOCATIONS IN THE MIDDLE OF THE SIDES. ACFT FUEL RT FUEL CELL HAD A SLOW LEAK SO THE CELL WAS REMOVED AND INSPECTED. USING AIR THERE WAS NO APPARENT LEAK, BUT WHEN FILLED WITH WATER, THE SIDES OF THE CELL ARE FOUND T
- [SDR CA130212027](https://openairdocs.org/sdr/CA130212027.md): Gasket · blown · Aug 14, 2012 · Bell 204B · Main Rotor Gearbox
  > (CAN) WHILE IN CRUISE FLIGHT THE PILOT GOT AN INDICATION OF NO TRANSMISSION OIL PRESSURE ON THE WARNING LIGHT AND PRESSURE GAUGE. HE PROCEEDED TO LAND. WHEN HE ROLLED THE THROTTLE TO IDLE THE BLADE SLOWED QUICKER THEN NORMAL HE THEN SHUT THE ENGINE DOWN AND
- [SDR CA080811004](https://openairdocs.org/sdr/CA080811004.md): Tuning Unit · cracked · Aug 8, 2008 · Bell 205A1 · Hydraulic System, Main
  > (CAN) TUBE ASSY WAS REPLACED EARLIER IN APRIL 2008 DURING WINTER MAINT. SINCE SINGLE HYDR SYS PARTS ARE HARD TO FIND ITEMS, SERVICEABLE PART WAS INSTALLED WITH APPROPRIATE CERTIFICATION. VISUAL INSP DIDN`T REVEALED ANY DAMAGE AND NO LEAK WAS NOTICED AT THIS TI
- [SDR CA080718001](https://openairdocs.org/sdr/CA080718001.md): Bearing · damaged · Jul 13, 2008 · Bell 205A1 · Main Rotor Mast/Swashplate
  > (CAN) DURING HELI-PORTABLE SEISMIC DRILLING OPS, UPON DESCENT WITH AN EXTERNAL LOAD, THE MASTER CAUTION WARNING INDICATION ILLUMINATED. THE PIC CHECKED THE CAUTION PANEL TO FIND A TRANSMISSION OIL PRESSURE CAUTION LIGHT ILLUMINATED AND THE TRANSMISSION OIL PRE
- [SDR CA080722001](https://openairdocs.org/sdr/CA080722001.md): Bearing · damaged · Jul 13, 2008 · Bell 205A1 · Main Rotor Gearbox
  > (CAN) UPON DESCENT WITH AN EXTERNAL LOAD, MASTER CAUTION WARNING INDICATION ILLUMINATED. THE PIC CHECKED THE CAUTION PANEL TO FIND A TRANSMISSION OIL PRESSURE CAUTION LIGHT ILLUMINATED, TRANSMISSION OIL PRESSURE GAUGE INDICATING ZERO PRESSURE. A POST-SHUTDOWN
- [SDR CA080702005](https://openairdocs.org/sdr/CA080702005.md): Turbine · damaged · Jun 26, 2008 · Bell 205B · Turbine Section
  > (CAN) PILOT CONDUCTED TAKE-OFF SCHEDULED TO CONDUCT LONGLINE OPERATIONS. APPROX 2 MINS AFTER TAKE-OFF THE PILOT HEARD A LOUD BANG FOLLOWED BY TORQUE YAWING. THE PILOT ENTERED AN AUTOROTATION AND LANDED THE ACFT ON A LOGGING ROAD. THE ACFT SUSTAINED MINOR DAMAG
- [SDR CA080606002](https://openairdocs.org/sdr/CA080606002.md): Blade · cracked · Jun 3, 2008 · Bell 205B · Tail Rotor Blades
  > (CAN) PILOT REPORTED PEDAL VIBRATIONS THROUGHOUT THE DAYS FLYING. AD-2008-10-03 CLEAN AND INSPECT T/R BLADES WAS SCHEDULED FOR THE 25 HRS AME INSP PORTION OF THE AD AFTER THE DAYS FLYING. AME INSPECTED T/R BLADES AND DETERMINED ONE BLADE TO BE UNSERVICEABLE
- [SDR CA080409005](https://openairdocs.org/sdr/CA080409005.md): Circuit Breaker · inoperative · Apr 9, 2008 · Bell 205A1 · AC Power Distribution System
  > (CAN) WHILE DOING A PREFLIGHT CHECK DURING FLIGHT TRAINING IT WAS NOTED THAT THE LT BOOST PUMP CIRCUIT BREAKER WAS NOT ABLE TO BE CYCLED. THE CIRCUIT BREAKER WAS REMOVED AND REPLACED. AFTER GOING THROUGH THE REST OF THE CIRCUIT BREAKER PANEL IS WAS NOTED THAT
- [SDR CA071203006](https://openairdocs.org/sdr/CA071203006.md): Mount · cracked · Dec 3, 2007 · Bell 205A1 · Engine Mount Section
  > (CAN) LT ENGINE TRIPOD AFT TUBING MOUNT FOUND CRACKED DURING 100 HRS INSPECTION JUST BELOW ENGINE MOUNTING PLATE AFT TUBE JUNCTION. NOTE: THIS MOUNT WAS MODIFIED IAW STC SH99-11, DART ADJUSTABLE MOUNT. (TC NR 20071203006)
- [SDR CA070828004](https://openairdocs.org/sdr/CA070828004.md): Bearing · worn · Aug 21, 2007 · Bell 204B · Tail Rotor Head
  > (CAN) PILOT WAS FLYING HELICOPTER AND FELT TWO SLIGHT YAWS TO THE RT APPROXIMATELY 30 TO 40 SECONDS APART. AT FIRST THE PILOT SUSPECTED IT MIGHT HAVE BEEN A GUST OF WIND, BUT THE SECOND YAW ALERTED THE PILOT TO A PROBLEM WITH THE TAIL ROTOR AS IT WAS ACCOMPANI
- [SDR CA070727003](https://openairdocs.org/sdr/CA070727003.md): O-Ring · failed · Jul 25, 2007 · Bell 205A1 · Hydraulic Power Accumulator, Main
  > (CAN) LOST OF HYDRAULIC IN FLIGHT, EMERGENCY LANDING, FAULT FOUND IN THE ACCUMULATOR, O-RING P/N MS28775-212 REPLACED A/C GROUND RUN AND LEAK CHECK COMPLETED AND RELEASED TO SERVICE. (TC NR 20070727003)
- [SDR CA080204006](https://openairdocs.org/sdr/CA080204006.md): Wire · shorted · Jun 14, 2007 · Bell 205A1 · Electrical Power System Wiring
  > (CAN) PILOT REPORTED SPARKS AND A SMALL AMOUNT OF SMOKE FROM THE OVERHEAD CONSOL. UPON INVESTIGATION IT WAS FOUND THAT THE LT OVERHEAD CONSOL PANEL HAD CHAFED THROUGH SEVERAL WIRES COMING UP THE CENTER POST OF THE WINDSHIELD CAUSING THE WIRES TO SHORT TO GROUN
- [SDR CA070506001](https://openairdocs.org/sdr/CA070506001.md): Nut · damaged · Apr 23, 2007 · Bell 204B · Tail Rotor Drive Shaft
  > (CAN) ON APRIL 23, 2007 DURING A TEST FLIGHT FOR MAINTENANCE THAT WAS PERFORMED, THE PILOT EXPERIENCED AN UNCONTROLLED YAW TO THE RIGHT WHILE IN A 4 FOOT HOVER. THE HELICOPTER WAS IMMEDIATELY SET DOWN ON THE TARMAC. THERE APPEARED TO BE A STEP WORN IN THE IN
- [SDR CA070321008](https://openairdocs.org/sdr/CA070321008.md): Beam · cracked · Mar 21, 2007 · Bell 205A1 · Fuselage Main, Structure
  > (CAN) WEB P/N 205-030-163-395 FOUND CRACKED AT INDUCTION BAFFLE SUPPORT WL 80.13. THE CRACK WAS APPROX 1 INCH IN LENGTH AND.5 INCH DOWN. REPAIR SCHEME IN PROGRESS THROUGH MFG. (TC NR 20070321008)
- [SDR 2006FA0001088](https://openairdocs.org/sdr/2006FA0001088.md): Adapter · damaged · Nov 19, 2006 · Bell 205A1 · Main Rotor System
  > DURING INSPECTION AND REGREASE OF THE M/R TRANS DRIVE SHAFT, A CHECK OF THE TORQUE OF THE DRIVE SHAFT ADAPTOR BOLT WAS ACCOMPLISHED AND IT WAS DISCOVERED THAT THERE WAS NO TORQUE, THAT THE BREAKER BAR`S WEIGHT BROKE THE BOLT LOOSE, REMOVED THE ADAPTOR AND FOUN
- [SDR CA070228005](https://openairdocs.org/sdr/CA070228005.md): Blade · missing · Sep 25, 2006 · Bell 205A1 · Engine Oil Cooler
  > (CAN) VIBRATION ON OIL COOLER BLOWER, FURTHER INVESTIGATION REVEALED ONE BLADE MISSING. SERVICEABLE OIL COOLER BLOWER INSTALLED, A/C RETURNED TO SERVICE. (TC NR 20070228005)
- [SDR CA060728003](https://openairdocs.org/sdr/CA060728003.md): Bearing · failed · Jul 14, 2006 · Bell 205A1 · Tail Rotor Drive Shaft
  > (CAN) THE TAIL ROTOR DRIVESHAFT HANGER HAD BEEN INSTALLED THE NIGHT BEFORE THE FAILURE. WE SUSPECT AN INNER COUPLING FAILURE. THE SUSPECT COUPLING HAD BEEN RECOATED JUST BEFORE INSTALLATION BY USING AN AMS2451/4 PROCESS. (TC NR 20060728003)
- [SDR CA060706002](https://openairdocs.org/sdr/CA060706002.md): Blade · cracked · Jul 4, 2006 · Bell 205A1 · Main Rotor Blades
  > (CAN) CRACK ON BOTH SIDES OF BLADE BOLT BORE. TRAVELLING IN CHORDWISE DIRECTION. THE LEADING EDGE CRACK TRAVELS RIGHT TO THE LEADING EDGE AND THE TRAILING EDGE CRACK IS APPROXIMATLEY 6 INCHES LONG. IT APPEARS ALL DOUBLERS ON THE LOWER PART OF THE BLADE ARE
- [SDR CA060622005](https://openairdocs.org/sdr/CA060622005.md): Cable · melted · Jun 21, 2006 · Bell 205A1 · Electrical Power System Wiring
  > (CAN) DURING TURN AROUND CHECK BY THE AME, THE WIRES TO THE STARTER GENERATOR WERE FOUND TO BE SUBJECTED TO HEAT DAMAGE. THERE WAS NO INDICATION TO THE PILOT OF ANY DEFECT. FURTHER INVESTIGATION FOUND THE STARTER GENERATOR WIRE BUNDLE BELOW THE ENGINE DECK
- [SDR CA060605010](https://openairdocs.org/sdr/CA060605010.md): Transmission · making metal · May 13, 2006 · Bell 204B · Main Rotor Gearbox
  > (CAN) METAL PARTICLES FOUND IN TRANSMISSION INTERNAL FILTER AFTER ROUTINE INSPECTION. NO CHIP LIGHT INDICATION. OIL DRAINED WITH NEW FILTER INSTALLED, AIRCRAFT RUN FOR ONE HOUR ON GROUND WITH METAL PARTICLES FOUND IN INTERNAL AND INLINE FILTER ASSY. NO CHIP
- [SDR CA060315007](https://openairdocs.org/sdr/CA060315007.md): Yoke · cracked · Mar 2, 2006 · Bell 205A1 · Fuselage, Seat/Cargo Attach Fittings
  > CRACKS ORIGINATING IN ATTACHMENT BOLT HOLES.
- [SDR CA051001001](https://openairdocs.org/sdr/CA051001001.md): Crosstube · cracked · Sep 30, 2005 · Bell 205A1 · Main Landing Gear Strut/Axle/Truck
  > (CAN) HIGH SKID GEAR. UPON LANDING THE FRONT CROSS TUBE CRACKED IN THE MIDDLE OF THE TUBE, BETWEEN THE MOUNTING SADDLES. FROM THE INFORMATION WE HAVE AT THIS TIME, THE AIRCRAFT WAS NOT HARD LANDED.
- [SDR CA050924001](https://openairdocs.org/sdr/CA050924001.md): Blade · failed · Sep 21, 2005 · Bell 205A1 · Turbine Engine Compressor Section
  > (CAN) AS THE A/C WAS APPROACHING STAGING WITH A SLING LOAD, THE PILOT HEARD A LOUD BANG FOLLOWED BY A LOUD SCREECHING NOISE FROM THE ENGINE. THE A/C LANDED IMMEDIATELY WITH POWER AND THE ENGINE SHUT DOWN. UPON FURTHER INVESTIGATION, ONE OF THE COMPRESSOR FIR
- [SDR CA040821001](https://openairdocs.org/sdr/CA040821001.md): Spherical Bearin · failed · Aug 20, 2004 · Bell 205A1 · Tail Rotor Head
  > (CAN) A/C WAS CLIMBING AFTER FILLING THE WATER BUCKET WHEN HE LOST COMPLETE TAIL ROTORAUTHORITY.THE A/C MADE SEVERAL 360 DEGREE TURNS AFTER COMING TO REST IN A CON FINED AREA. SUBSTANTIAL DAMAGE WAS DONE TOTHE MAIN ROTOR BLADES AS THEY STRUCK A TREE UPON LANDI
- [SDR CA040901005](https://openairdocs.org/sdr/CA040901005.md): Volt Regulator · failed · Jul 18, 2004 · Bell 204B · AC Regulator
  > (CAN) VOLTAGE REGULATOR DELIVERING OVER 30 VOLTS. THE AIRCRAFT WAS READY TO TAKE OFF WHEN THE PILOT SMELLED A STRONG ODOR IN THE COCKPIT. ASSUMING IT WAS THE BATTERY, HE SHUT DOWN THE ENGINE. IN THE INSPECTION THE BATTERY WAS FOUND TOO HOT AND THE VOLTAGE DELI
- [SDR CA040901003](https://openairdocs.org/sdr/CA040901003.md): Blade · cracked · Jul 4, 2004 · Bell 204B · Main Rotor Blades
  > (CAN) MAIN ROTOR BLADE FOUND CRACKED ON THE TOP SURFACE 90 INCHES FROM THE TIP. ABOUT 70 HOURS BEFORE, A CRACK ON THE BLADE PAINT WAS FOUND, AT THAT TIME NO CRACK WAS FOUND IN THE BLADE SKIN. IAW ASB204-49-96 PT I AND II, THE BLADE WAS INSPECTED DAILY (PART I
- [SDR CA040203011](https://openairdocs.org/sdr/CA040203011.md): Shaft · worn · Jan 27, 2004 · Bell 204B · Fuel Control/Reciprocating Engines
  > (CAN) UPON SUSPECTING A PROBLEM WITH FUEL CONTROL UNIT. REMOVED FCU FROM THE ENGINE TO INSPECT THE SPLINES IAW MFG SBT5313-107. FOUND THE INTERNAL SPLINES KNIFE EDGED AND VERY CLOSE TO TOTAL FAILURE OF THE FCU. THIS WOULD HAVE LEAD TO THE FAILURE AND SHUTDOWN
- [SDR CA040209012](https://openairdocs.org/sdr/CA040209012.md): Shaft · worn · Jan 27, 2004 · Bell 204B · Fuel Control/Turbine Engines
  > (CAN) FUEL CONTROL RECEIVED FROM CUSTOMER FOR INSPECTION FOLLOWING PREVIOUS RECORDS ABOUT PUMP FAILURE (WSDR 20040128006). FUEL CONTROL HAS TSO- 3195.3 AND WAS OPERATING ON EXTENSION TIME DUE TO A GOOD PERFORMANCES. IT WAS REMOVED FROM A/C FOR INSPECTION IAW
- [SDR 2004FA0000148](https://openairdocs.org/sdr/2004FA0000148.md): Fitting · damaged · Jan 9, 2004 · N4750R · Bell 205A1 · Engine Mount Section
  > UPON OPENING PACKED FOR FITTING ASSEMBLY FOUND THREADS ON LONG SIDE OF FITTING PULLED LOOSE. PART REJECTED BEFORE INSTALLATION.
- [SDR CA030915008](https://openairdocs.org/sdr/CA030915008.md): Boot · torn · Sep 7, 2003 · Bell 205A1 · Engine/Transmission Coupling
  > (CAN) DURING THE INSPECTION AFTER THE LAST FLIGHT OF THE DAY, THE ENGINEER INSPECTED THE MAIN DRIVESHAFT BOOTS FOR LEAKAGE. THERE WAS NO VISUAL SIGN OF A GREASE LEAKAGE. AS THE ENGINEER PUT HIS HAND UNDER THE, ENGINE SIDE, DRIVESHAFT COUPLING, HE FELT A BUILT
- [SDR CA031001006](https://openairdocs.org/sdr/CA031001006.md): Fitting · cracked · Aug 25, 2003 · Bell 205A1 · Fuselage Main, Attach Fittings
  > (CAN) PART REMOVED FROM SERVICE.NEW PART INSTALLED.
- [SDR CA030912003](https://openairdocs.org/sdr/CA030912003.md): Gear · failed · Jul 28, 2003 · Bell 205A1 · Accessory Gearboxes
  > (CAN) A/C PERFORMING NORMAL APPROACH. DURING FINAL, A LIGHT WHINING SOUND HEARD AS POWER APPLIED. AS POWER INCREASED, SOUND INCREASED. AT APPROX 8 FT FROM TOUCHDOWN, ENG STOPPED, & CHIP CAUTION LIGHT ILLUMINATED. CONTROL MAINTAINED HELICOPTER LANDED WITHOUT IN
- [SDR AUS20030596](https://openairdocs.org/sdr/AUS20030596.md): Compressor · fod · Apr 3, 2003 · Bell 205A1 · Turbine Engine Compressor Section
  > (AUS) ENGINE VARIABLE INLET GUIDE VANES (VIGV) AND COMPRESSOR BLADES DAMAGED BY FOD. INVESTIGATION FOUND THAT DAMAGE HAD BEEN CAUSED BY AN OBJECT WITH A DIAMETER OF APPROXIMATELY 3.175MM TO 4.762MM(0.125IN TO 0.1875IN). AN OBJECT OF THIS SIZE COULD NOT PASS
- [SDR CA021113003](https://openairdocs.org/sdr/CA021113003.md): Nozzle · unapproved part · Oct 31, 2002 · Turbine Section
  > (CAN) MILITARY PARTS FOUND INSTALLED ON ENGINE S/N LE-07616. INSTALLED PART MANUFACTURER CODE NUMBER IS 81996 (US MILITARY). IT SHOULD BE 91547. (HONEYWELL OEM). ENGINE S/N LE-07616 OVERHAULED ON 31 MARCH 1993 AT ENGINE TSN:2979.051. 2ND GP NOZZLE P/N 1-12
- [SDR AUS20021231](https://openairdocs.org/sdr/AUS20021231.md): Fitting · faulty · Oct 15, 2002 · Bell UH1H · Fuselage Main, Attach Fittings
  > (AUS) TAILBOOM LH LOWER ATTACHMENT FITTING ON FUSELAGE HAD OVERSIZE HOLES ALLOWING THE HILOK' PINS TO LOOSEN. SUSPECT CAUSED BY POOR REPAIR WORK.
- [SDR CA021001010](https://openairdocs.org/sdr/CA021001010.md): Drive Shaft · chafed · Sep 20, 2002 · Bell 205A1 · Tail Rotor Drive Shaft
  > (CAN) AT TIME OF RE-GREASING THE T/R DRIVESHAFT COUPLINGS. T/R DRIVESHAFT WAS REMOVED FROM TUNNEL UNDER ENGINE. FOUND CONTACT WAS MADE WITH TUNNEL AT ENTRANCE DIRECTLY AFT OF TRANSMISSION. SHAFT IS OF NEWER STYLE -011 WHICH IS OF A GREATER DIAMETER THAN THAT O
- [SDR CA021007007](https://openairdocs.org/sdr/CA021007007.md): Hanger Assy · cracked · Sep 18, 2002 · Bell 205A1 · Tail Rotor Drive Shaft
  > (CAN) HANGER CRACKED AT BOTH ATTACH POINTS FOR THE FLEX COUPLING ATTACH.
- [SDR CA021003007](https://openairdocs.org/sdr/CA021003007.md): Hose · leaking · Sep 13, 2002 · Bell 204B · Hydraulic System, Main
  > (CAN) HOSE ASSEMBLY FAILED RESULTING IN LOSS OF HYDRAULIC FLUID. THE LOSS OF FLUID RESULTED IN LOSS OF HYDRAULIC BOOST TO FLIGHT CONTROLS. AIRCRAFT WAS LANDED UNEVENTFULLY WITHOUT HYDRAULIC BOOST. THE HYDRAULIC LINE EXHIBITED NO SIGNS OF LEAKAGE PRIOR TO FAILU
- [SDR CA020918006](https://openairdocs.org/sdr/CA020918006.md): Bulkhead · cracked · Sep 6, 2002 · Bell 204B · Fuselage Main, Bulkhead
  > (CAN) THE ROTOR CONTROL BELLCRANK BULKEAD CRACKED IN MULTIPLE PLACES.
- [SDR CA020918010](https://openairdocs.org/sdr/CA020918010.md): Bulkhead · cracked · Sep 2, 2002 · Bell 204B · Rotorcraft Tail Boom
  > (CAN) T/R FLIGHT CONTROL BELLCRANK SUPPORT ATTACHES TO BULKHEAD. THE BULKHEAD IS REINFORCED BY LOWER ANGLE AND UPPER ANGLE, SUSPECT THAT THE LOWER ANGLE CRACKED PROBABLY DUE TO CORROSION (NOT VERIFIED). THIS ALLOWED THE SUPPORT TO MOVE AND EVENTUALLY CRACKED
- [SDR CA020729002](https://openairdocs.org/sdr/CA020729002.md): Indicator · failed · Jul 11, 2002 · Bell 205A1 · Main Rotor Indicating System
  > (CAN) FROM REPORTS: THE AIRCRAFT WAS HOVERING WITH A WATER BUCKET OVER A FIRE. ROTOR SPEED DECAYED AND PILOT MADE A FORCED LANDING IN A CLEARING. THE AIRCRAFT LANDED VERY HARD AND ROLLED ON TO ITS RIGHT SIDE. PILOT CRAWLED OUT AND SUSTAINED MINOR INJURIES. THE
- [SDR CA020918008](https://openairdocs.org/sdr/CA020918008.md): Engine · flamed out · Jul 10, 2002 · Bell 205A1 · Engine (Turbine/Turboprop)
  > (CAN) DURING ROUTINE FLIGHT AFTER FUELING FROM A SUPPLIED SEALED DRUM OF PRE-MIXED JET FUEL (FSII) ADDED. THE ENGINE FLAMED OUT AND A FORCED LANDING RESULTING IN NO DAMAGE TO THE HELICOPTER.
- [SDR CA020726017](https://openairdocs.org/sdr/CA020726017.md): Blade · bent · Jul 1, 2002 · Bell 205A1 · Main Rotor Blades
  > (CAN) THE LT WING TIP OF A CL-415 WATER BOMBER CONTACTED THE FORWARD ROTOR BLADE OF THE 205. THE 205 WAS PARKED AND TIED DOWN. THE CL-415 WAS DESCRIBED AS TRAVELLING AT A "SLOW TAXI SPEED". ONE BLADE SUSTAINED MINOR DAMAGE (REPAIRABLE) AT TIP. NO OTHER DAMAGE
- [SDR CA020627007](https://openairdocs.org/sdr/CA020627007.md): Fuel Cell · contaminated · Jun 20, 2002 · Bell 205A1 · Aircraft Fuel Distribution System
  > (CAN) CRYSTALS WERE FOUND IN THE FUEL CELL WHILE IT WAS FIRE-FIGHTING HOUSE LAKE FIRE. THE CRYSTALS WERE FOUND DUE TO A BLOCKED EJECTOR PUMP. SOURCE OF THE CRYSTALS IN UNKNOWN. A SAMPLE OF THE CRYSTALS WAS PROVIDED FOR ANALYSIS. IT WAS DETERMINED THAT THE
- [SDR CA020607007](https://openairdocs.org/sdr/CA020607007.md): Engine · failed · Jun 2, 2002 · Bell 205A1 · Engine (Turbine/Turboprop)
  > (CAN) A/C WAS IN PROGRESS OF FIREFIGHTING WHEN ENGINE 'FIRE WARNING' ILLUMINATED. AFTER VERIFYING FIRE VIBRATION, PILOT DECIDED TO CARRY OUT AN EMERG LDG. ON DESCENT FROM AP PROX 150 FEET, ENGINE CHIP LIGHT CAME ON AS WELL AS ENGINE OIL LOW PRESSURE WARNING LI
- [SDR CA020611003](https://openairdocs.org/sdr/CA020611003.md): Valve Seat · failed · May 30, 2002 · Bell 205A1 · Main Rotor Gearbox
  > (CAN) DURING THE SCHEDULED 25 HOUR INSPECTION THE AME NOTED THAT THE VALVE SEAT HAD UNSCREWED ITSELF FROM THE FILTER BODY AND DAMAGED THE FILTER, WAFER. THE VALVE SEAT WAS SECURED AND THE FILTER, WAFER WAS REPLACED.
- [SDR CA020507009](https://openairdocs.org/sdr/CA020507009.md): Mount · cracked · Apr 30, 2002 · Bell 205A1 · Main Rotor Gearbox
  > (CAN) DURING MAIN ROTOR TRANSMISSION REMOVAL FOUND CRACK EXTENDING FROM LOWER MOST BOLT HOLE OF 5TH MOUNT ATTACHMENT ANGLE, RT SIDE OF TRANSMISSION PYLON AREA.CRACK REPAIRED I.A.W. THE BELL MEDIUM STRUCTURAL REPAIR MANUAL (BHT-MED-SRM-1) SECTION 4-6-3, "MAIN B
- [SDR CA020507010](https://openairdocs.org/sdr/CA020507010.md): Beam · cracked · Apr 17, 2002 · Bell 205A1 · Fuselage Miscellaneous Structure
  > (CAN) SMALL CRACK FOUND ON TOP "T" CAP OF LT VERTICAL MAIN BEAM ASSEMBLY. CRACK WAS OBSERVED WERE "T" CAP TRANSITIONS FROM UNDER THE ENGINE DECK GOING FORWARD THROUGH THE AFT SIDE OF THE MAIN ROTOR PYLON AREA.NEW "T" CAP INSTALLED IAW BELL MEDIUM STRUCTURAL RE
- [SDR CA020501002](https://openairdocs.org/sdr/CA020501002.md): Fitting · cracked · Apr 11, 2002 · Bell 205A1 · Main Rotor Transmission Mount
  > (CAN) CRACK FOUND AT BOTTOM OF BEAM (FITTING HOUSING) WHERE 5TH MOUNT IS HOUSED, 3/4 INCH LONG. BELL MAINTENANCE MANUAL SPECIFIES NO CRACKS IN THIS AREA.

Next page: https://openairdocs.org/engine/lycoming-t5313b/reports.md?page=2

## 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 = 'T5313B'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/engine/lycoming-t5313b/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.