TPE331Honeywell (Garrett) TPE331

Parts most often named Engine (412) · Bearing (11) · Bearing Race (5) · Plenum (3)

ENGINE WAS RECEIVED POST IN-FLIGHT EMERGENCY. DISASSEMBLY REVEALED THAT THE BULL GEAR SEPARATED AND BROKE THROUGH THE ACCESSORY DRIVE HOUSING. THE DEBRIS WAS THEN INGESTED THROUGH THE INLET AND TRAVELED THROUGH THE ENTIRE GAS PATHWAY CAUSING DAMAGE THROUGHOUT THE ENGINE.

DURING DESCENT, ENGINE FLAMED OUT @ 7000 FT MSL. THROTTLES @ FLIGHT IDLE, ENGINE NTS SURGING, EGT 428, RPM DROPPED TO 38%, INITIATED FEATHER OF ENGINE. SINGLE ENGINE LANDING UNEVENTFUL. CAUSE TBD.

DURING DESCENT, #2 ENGINE FLAMED OUT @ 7000 FOOT MSL, THROTTLES @ F.I. ENGINE NTS SURGING, EGT 428, RPM 38%, FEATHERED ENGINE. SINGLE ENGINE LDG UNEVENTFUL. CAUSE TBD

Parts most often named Fuel Control (60) · Bypass Valve (25) · P3 Line (19) · Fcu (11)

ON LANDING, THE PILOTS NOTICED THE LEFT ENGINE HAD SHUT DOWN. THEY WERE ABLE TO SECURE THE ENGINE AND CLEAR THE RUNWAY, BUT NEEDED TO BE TOWED BACK TO THE MAINTENANCE HANGAR. POST FLIGHT MAINTENANCE RUNS DISCOVERED THE SUSPECTED FAILURE OF THE UNDERSPEED GOVERNOR IN THE FUEL CONTROL UNIT.

(CAN) CREW WERE LINED UP FOR TAKEOFF, AS THEY ADVANCED THE SPEED LEVERS THE L/H ENGINE SHUT DOWN. THE AIRCRAFT TAXIED BACK TO THE MAINTENANCE HANGAR ON ONE ENGINE AND MAINTENANCE INVESTIGATION FOUND THE PRIMARY ONLY SOLENOID VALVE ON THE L/H ENGINE HAD FAILED, THE SOLENOID BODY HAD PARTIALLY SEPARATED FROM THE BASE THAT THE FUEL FLOWS THROUGH DUE TO A SHEARED SCREW (2 SCREWS HOLD THE UNIT TOGETHER) THIS IN TURN CAUSED A LARGE FUEL LEAK LIMITING FUEL TO THE ENGINES FUEL NOZZLES. (TC# 20190801009)

GEAR PN 896884-1 APPARENTLY FRACTURED AT THE KEYWAY ALLOWING THE MAIN SHAFT DRIVE TO THE FUEL CONTROL DRIVE TRAIN TO BECOME DISENGAGED CAUSING AN UNCOMMANDED ENGINE SHUTDOWN DUE TO LACK OF FUEL.

Parts most often named Fuel Control (77) · Fcu (41) · Fuel Contl Unit (16) · Drive Shaft (6)

FUEL CONTROL UNIT P/N 897801-2 [S/N removed] WAS INSPECTED IN ACCORDANCE WITH WOODWARD INSPECTION CRITERIA CONTAINED IN WG60183. “VESPEL” STUB DRIVESHAFT PN: 3499-096 INTERNAL SPLINES WERE FOUND WORN BEYOND COMPONENT MAINTENANCE MANUAL LIMITS.

FUEL CONTROL UNIT P/N 897801-2 [S/N removed] WAS RECEIVED FOR REPORTED LOW FUEL FLOW DURING ENGINE OPERATION. THE FUEL CONTROL UNIT WAS INSPECTED IN ACCORDANCE WITH COMPONENT MAINTENANCE MANUAL WG60183. DISASSEMBLY REVEALED SEVERELY WORN STUB SHAFT P/N 3499-096 ON FCU. THE SEVERITY OF THE STUB SHAFT WEAR WOULD CAUSE THE FUEL CONTROL NOT TO TURN (SPIN) AS NEEDED FOR NORMAL OPERATION, LIMITING FUEL FLOW TO 180 +/ - 20 POUNDS PER HOUR.

FUEL CONTROL UNIT P/N 897801-2, [S/N removed] WAS RECEIVED FOR PRECAUTIONARY SPLINE INSPECTIONS DUE TO CUSTOMER REPORTED ACCELERATED STUB SHAFT SPLINE WEAR. DISASSEMBLY AND INSPECTION REVEALED STUB DRIVE SHAFT P/N 3499-096 WITH ACCELERATED WEAR ON INTERNAL SPLINES.

Parts most often named Scavenge Pump (15) · Pump (12) · Line (10) · Adapter (10)

DURING LANDING ROLLOUT, THE ENGINE LOST OIL PRESSURE, RESULTING IN A LOSS OF POWER AND ENGINE SHUTDOWN. TROUBLESHOOTING IDENTIFIED AN OCCLUDED MAIN SHAFT OIL TRANSFER TUBE. CLEANED THE MAIN SHAFT OIL TRANSFER TUBE IN ACCORDANCE WITH TPE331-11 MM 72-00-25, CHAPTER 72-10-14. GROUND OPS CHECK GOOD.

ENGINE REMOVED FOR DISCOLORED OIL AND EXCESSIVE OIL CONSUMPTION, ONE QUART EVERY TWO HOURS. INSPECTION REVEALED OIL SCAVENGE PUMP ASSEMBLY SCORED (PN: 3108282-2). SCAVENGE PUMP GEAR SHAFT DRIVE KEY SLOT ELONGATED (PN: 3108286-1) DRIVE KEY SHEARED (PN: 3108289-1). TURBINE SCAVENGE PUMP ASSEMBLY SPUR GEAR SHAFT PITTED (PN: 3102270-4).

PILOT REPORTED NR 1 ENGINE LOST OIL. MX TROUBLESHOT AND LOCATED A LEAK AT 7/16 OIL MANIFOLD TO PROP GOVERNOR LINE. MX REMOVED AND REPLACED LINE AND REPOSITIONED MANIFOLD AS REQUIRED FOR FIT. POST ACTION OPS AND LEAK CHECKED GOOD AND [S/N removed] OIL.

Parts most often named Seal (39) · Turbine Wheel (18) · Turbine Blades (10) · Blade (9)

PILOT REPORTED LOUD BANG IN FLIGHT FOLLOWED BY ACTIVATION OF NTS SYSTEM; PILOT SECURED ENGINE AND LANDED. ENGINE REMOVED/REPLACED IN THE FIELD AND TRANSPORTED TO MAIN MX BASE FOR TEARDOWN. MX PERSONNEL FOUND DURING TEARDOWN THAT SEVERAL BLADES ON THE 1ST HPT WHEEL ASSY FAILED AND BROKE AWAY FROM THE DISK AT THE FIR TREE ATTACHMENT. ENGINEERING/METALLURGICAL ANALYSIS HAS BEEN REQUESTED.

E2 SUFFERED UNCONTAINED ENG FAILURE ON CLIMB OUT. 2ND STAGE TURBINE DISK FAILED & WAS THROWN FROM THE ENG THROUGH THE LT & RT SIDES OF THE ENG. APPROX 1/4 OF THE 2ND STAGE TURBINE DISK PENETRATED THE CABIN & WAS FOUND ON THE CARGO FLOOR.

(CAN) DURING WINTER MAINTENANCE BOROSCOPE INSPECTION DAMAGE TO THE 1ST STAGE COMPRESSOR TURBINE BLADE WAS DISCOVERED. THIS WAS MISSING BLADE SECTIONS AND CRACKS. ENGINE REMOVED AND SENT TO CD AVIAITION REPAIR SHOP FOR EVALUATION. PLEASE SEE ATTACHED. (TC# 20141022006)

Parts most often named Bearing (16) · Impeller (13) · Plenum (10) · Stator Vane (9)

ROUTINE SOAP SAMPLE WAS FLAGGED FOR M50 STEEL (BEARING MATERIAL) IN FILTER. ENGINE WAS REMOVED AND SENT TO A REPAIR STATION, WHERE IT WAS FOUND THAT THE COMPRESSOR BEARING WAS FAILING. THE ENGINE WAS REPAIRED AND REINSTALLED AND THE AIRCRAFT RETURNED TO [S/N removed].

(CAN) ENGINE CAME INTO THE TURBINE SHOP FOR A ROUTINE 7000 HR CAM INSPECTION AND WHEN THE ENGINE WAS BEING DISMANTLED TO START THE INSPECTION OF THE ENGINE THE NR 2 IMPELLER WAS NOTICED TO HAVE A BROKEN BLADE ON IT.

(CAN) ENGINE P-44016 WAS BROUGHT INTO THE TURBINE SHOP FOR ROUTINE OVERHAUL AND WHEN THE ENGINE WAS TAKEN APART THE COMPRESSOR HOUSING WAS DAMAGED IN THE AREA WERE THE NR 2 IMPELLER SITS AND RIDES IN. THIS AREA HAS A SPRAY METAL REPAIR THAT IS DONE TO BUILD UP THE AREA THAT SEATS THE NR 2 IMPELLER WHEN GROUND IN.

Parts most often named Chip Detector (24) · Bearing (15) · Housing (8) · Chip Light (4)

ENG WOULD NOT START. ROTATION OF PROPELLER BY HAND PRODUCED A GRINDING SOUND. ENG GEARBOX WAS ACCESSED. THE MAIN SHAFT FUEL DRIVE SPUR GEAR WAS FOUND CRACKED IN HALF & SEPARATED. SEPARATED SPUR GEAR CAUSED LOSS OF FUEL DRIVE, CAUSING ENG TO NOT START. THE GEARBOX WAS RE-ASSEMBLED USING A [S/N removed] SPUR GEAR.

OUTPUT HSG CRACK LINE MX WAS DOING A ROUTINE INSP ON ENGINE, WHEN ONE OF THE MECHANICS NOTICED A CRACK ON THE SIDE OF THE ACCY DRIVE HSOUSING. THE TURBINE SHOP WAS NOTIFIED OF THE ISSUE AND UPON FURTHER INSP, THE ENG WAS DETERMINED TO HAVE TO COME OFF TO BE REPLACED. THE ENGINE WAS REPLACED AND THE ACFT WAS PUT BACK INTO [S/N removed]. THE ENGINE WAS FORWARDED TO THE TURBINE SHOP FOR REPAIR.

(CAN) TACH/GEN IDLER ASSY DUAL SPUR GEAR, CENTER ANTI FRICTION BEARING FOUND WITH AN UNUSUALLY HIGH AMOUNT OF RADIAL PLAY AND WAS EXTREMELY ROUGH WHEN TURNED OVER BY HAND. THE ENGINE WAS REMOVED DUE TO CARBON STEEL PLATELETS FOUND IN THE OIL SAMPLE.

Parts most often named Gear (13) · Bearing (11) · Gearbox (7) · Idler Gear (3)

PILOT REPORTED E2 FAILURE SPOOL BACK FOLLOWED BY CHIP DETECTOR LIGHT. MAINTENANCE REMOVED AND REPLACED 1ST IDLER, DIAPHRAGM, AND PLANETARY GEARS.

(CAN) ENGINE HAD A SOAP SAMPLE COME BACK THAT INDICATED MAJOR ALLOY STEAL, MANUFACTURER INDICATED ON THE SOAP IT REQUIRED INSPECTION RIGHT AWAY DUE TO THE FINDINGS OF THE SOAP SAMPLE. THE ENGINE WAS FORWARDED TO AN ENGINE SHOP FOR EVALUATION AND THE PART THAT WAS FOUND TO CAUSE THE ISSUES WAS THE PLANETARY CARRIER. THE CARRIER HAD MULTIPLE CRACKS ON IT DEFINING A MAJOR FAILURE WAS EVIDENT. THE ENGINE WAS REPAIRED AND WILL BE PUT BACK INTO [S/N removed]. (TC# 20190614012)

CARRIER RECIEVED REPORT OF BAD SOAP SAMPLE. CARRIER DISASSEMBLED ENGINE GEARARBOX AND FOUND BROKEN OIL NOZZLE ASSEMBLY IN INTERMEDIATE HOUSING AND GEAR ASSEMBLY - ACCESSORY GEAR AND DRIVE IDLER HOUSING ASSEMBLY.

Parts most often named Line (13) · Valve (11) · Filter (6) · Fuel Line (6)

(CAN) WHILE REMOVING LT STARTER/GEN FOR INSPECTION PURPOSES IT WAS FOUND THE FUEL LINE (P/N 3102762-1) WAS RUBBED ALMOST ALL OF THE WAY THROUGH BY THE PROPELLER GOVERNOR. AFTER REMOVAL OF THE FUEL LINE IT WAS THEN FOUND THAT THE FUEL LINE WAS RUBBING ON THE OIL LINE THAT TAKES THE OIL TO THE PROPELLER CONTROL. ITHIS WAS ABOUT 1/3 TO 1/2 THE WAY THROUGH. BOTH LINES WERE REMOVED AND REPLACED.

(CAN) UPON LANDING, THE CREW REPORTED TO MAINTENANCE THAT FUEL WAS LEAKING BY THE LT ENGINE LOWER COWLING FROM THE OIL TO FUEL HEATER. MAINTENANCE REPLACED FUEL LINE BY ENGINE MOUNT THAT HAD CHAFED THROUGH.

(CAN) AIRCRAFT RETURNED TO BASE AS LT ENGINE COULD NOT MAKE FULL POWER. LT ENGINE FUEL BOWL TEE FITTING FOUND CRACKED. FITTING REPLACED AND ACFT RETURNED TO [S/N removed]. ALSO CONNECTOR PLUG WIRE CONTROLLING THE BYPASS VALVE WAS REPAIRED AT THIS TIME.

Parts most often named Starter Gen (17) · Bearing (16) · Brushes (4) · Adapter (2)

(CAN) LEFT STARTER GENERATOR FAILED APPROXIMATELY 20 MINUTES AFTER DEPARTURE. GENERATOR WENT OFF-LINE AND A LOW RUMBLE AND VIBRATION WAS NOTED COMING FROM THE LT ENGINE. ACFT RETURNED TO BASE AND UNIT WAS REPLACED. GROUND RUN C/O, ALL SYSTEMS CHECKED [S/N removed].

(CAN) DURING A MAINTENANCE INSPECTION ON THE LT ENGINE STARTER GENERATOR ASSY, THE MOUNTING ADAPTER WAS OBSERVED WITH A CRACK THROUGH THE WEB ADJACENT TO A MOUNTING HOLE.

(CAN) APPROACHING THE AIRPORT, PILOTS NOTICED THE "START GEN" ANNUNCIATOR TO ILLUMINATE (LIGHT UP). A FEW MINUTES AFTERWARDS, THEY SAW SPARKS COMING OUT FROM THE ENGINE. FOR PRECAUTION, THEY SHUTDOWN THE ENGINE AND THEY LANDED WITHOUT ANY PROBLEMS. AFTER VERIFICATION THE START GEN WAS FOUND SEIZED THE INTERNAL BEARINGS FAILED.