206JetRanger

Parts most often named Bearing (16) · Transmission (9) · Gear (8) · Drag Pin (7)

(CAN) ACFT WARNING SYSTEM INDICATED METAL CHIP GENERATION INSIDE MAIN TRANSMISSION. TRANSMISSION REMOVED FROM ACFT AND INVESTIGATION FOUND DUPLEX BEARING DETERIORATION.

TRANSMISSION ARRIVED TO OUR FACILITY FOR REPAIR DUE TO METAL PARTICLES FOUND IN FREEWHEEL AND ON TRANSMISSION OIL FILTER MAGNETIC PLUG. DURING OUR INSPECTION, WE FOUND THAT NUT PN 206-040-045-001 WAS INSTALLED INCORRECT, THE RESULT OF THIS WAS 2 BROKEN TANGS ON THE NUT. THE 2 BROKEN TANGS WERE LATER FOUND INSIDE THE TRANSMISSION.

(CAN) DURING A DAILY INSPECTION, A CRACKED NUT WAS OBSERVED WHICH IS LOCATED ON THE BOLT THAT CONNECTS THE TRANSMISSION MOUNT TO THE FORWARD DECK FITTING.

Parts most often named Governor (70) · Control Lever (3) · Drive Gear (2) · Bearing (2)

(CAN) AIRCRAFT WAS IN FLIGHT AND PILOT NOTICED A DROP IN ENGINE RPM FROM 100% TO 90%. STARTED DECENT ON A BUSH ROAD. GOVERNOR WAS REPLACED WITH A [S/N removed] UNIT. NO DAMAGE OR INJURY (TC# 20190716006)

(CAN) DURING ACFT RUN UP AND PRE TAKEOFF CHECKS THE PILOT WAS UNABLE TO OBTAIN FULL MAIN ROTOR RPM. THE ACFT WAS SHUTDOWN AND MAINTENANCE CONTACTED. THE AME FOUND THE ENGINE GOVERNOR ARM TO BE SEIZED. THE ENGINE GOVERNOR ASSEMBLY WAS REPLACED AND THE ACFT RETURNED TO [S/N removed]. THE TORQUE ON THE NUT SECURING THE ARM TO THE GOVERNOR WAS CHECKED AND FOUND CORRECT, IF THIS NUT IS OVER TIGHTENED IT CAN CAUSE BINDING.

(CAN) PILOT REPORTED THAT GOVERNOR BEEP RANGE WAS OUT OF TOLERANCE. GOVERNOR COULD NOT BE ADJUSTED TO WITHIN LIMITS. GOVERNOR REPLACED.

Parts most often named Bearing (16) · Lever Assy (11) · Link Idler (11) · Mast (9)

ACFT LANDED ON LOAD TRUCK. ACFT RECEIVED FUEL AND LOAD. PILOT FELT VIBRATION AND SHUTDOWN ACFT AND FOUND MAST POLE BROKEN.

(CAN) DURING 100HR INSPECTION, METAL FOUND ON ALL 3 M/R TRANSMISSION MAGNETIC CHIP DETECTORS. NOT ENOUGH METAL FOR A COCKPIT CHIP INDICATION. METAL ALSO FOUND IN M/R GEARBOX OIL FILTER. TRANSMISSION ASSY AND MAST ASSY REMOVED FOR INSPECTION, M/R MAST BEARING INNER RACE FOUND SPALLING. BEARING REPLACED WITH NEW. TRANSMISSION AND TRANSMISSION OIL COOLER FLUSHED TO REMOVE METAL CONTAMINATION.

(CAN) DURING ROUTINE INTERNAL MAST CORROSION, INTERNAL DAMAGE WAS FOUND 1.5" TO 2" FROM THE TOP OF THE MAST, INTERNALLY. LPI AND MPI COMPLETED AND TESTED OK BUT MAST WAS REJECTED DUE TO VISUAL DAMAGE.

Parts most often named Nozzle (13) · Bearing (7) · Wheel (6) · Turbine (6)

(CAN) THE PILOT HAD REPORTED [tail no. removed] LOCKUP. DURING MAINTENANCE THE ENGINE WAS DISASSEMBLED TO HAVE THE ENGINE GEARBOX REPAIRED AND TO SEND THE TURBINE FOR INSPECTION TO DETERMINE THE CAUSE OF THE [tail no. removed] LOCKUP. THE TURBINE WAS SENT FOR INSPECTION. DURING THE INSPECTION THEY DISCOVERED A CRACK IN THE 3RD STAGE TURBINE WHEEL. THIS IS WHAT THEY BELIEVE IS THE CAUSE OF THE [tail no. removed] LOCKUP.

(CAN) DURING LANDING, THE PILOT NOTICED POWER LOSS OF THE NR 2 ENGINE. THE ACFT MADE AN UNEVENTFUL LANDING. A VISUAL INSPECTION OF THE ENGINE SHOWED THE EXHAUST DUCT INNER CRACKED WITH MATERIAL MISSING. THERE WAS NO INDICATION OF FRACTURED PT BLADES. THE POWER AND COMPRESSOR TURBINES ROTATED FREE. A BORESCOPE INSPECTION IS SCHEDULED.

(CAN) DURING DEPARTURE FROM AIRFIELD, FLIGHT CREW PASSING THROUGH 800 FT AGL NOTED THE TURBINE [tail no. removed] SPEED INCREASING FOLLOWED BY A LOUD HUMMING NOISE. THEY THEN HAD AN ENGINE CHIP LIGHT. THEY LANDED THE ACFT IMMEDIATELY. UPON MAINTENANCE ARRIVAL IT WAS NOTED THAT A LARGE AMOUNT OF OIL LEAKING FROM THE TURBINE.

Parts most often named Blade (54) · Bolt (3) · Washer (3) · Counterweight (1)

DURING CLIMB 850 FEET, LATERAL VIBRATION CAME. LANDING PROCEDURES, AFTER VISUAL INSPECTION MAIN ROTOR BLADE TIP CAME OUT. AFTER DEEP INSPECTION AT HOME BASE, TELL-TALE WEIGHT SHEARED OFF INSIDE THE SPAR. CAUSING BLADE UNSERVICEABLE AFTER THIS EVENT.

(CAN) LOSS OF M/R BLADE TELL-TALE WEIGHT CAUSED LATERAL VIBRATIONS. PILOT FOUND THE TIP CAP YIELDED FROM MOUNTING, BUT STILL ATTACHED BY LOWER FORWARD SCREW.

(CAN) THE WEIGHT SEPARATED IN FLIGHT DAMAGED THE BLADE TIE-DOWN TIP CAP. MFG TECHNICAL BULLETIN 206-11-197, REV. REFERS TO THIS.

Parts most often named Seal (10) · Clutch (9) · Coupling (8) · Drive Shaft (6)

THE FREEWHEELING UNIT WAS FAILING CAUSING THE MAIN GEARBOX CHIP LIGHT TO INTERMITTENTLY ILLUMINATE. WHEN THE CHIP DETECTORS WERE INSPECTED THERE WAS NO METAL NOTED. NOTHING APPEARED IN THE OIL FILTER OR SCREEN DURING THE [S/N removed] CHECK.

(CAN) DURING TRAINING, IT WAS NOTICED THAT THE TACH NEEDLES DID NOT SEPARATE WHEN THE THROTTLE WAS ROLLED BACK TO IDLE. FREEWHEEL ASSY WAS REMOVED AND SENT TO O/H SHOP FOR INSPECTION. DURING INSPECTION CLUTCH ASSY WAS DEEMED UNSATISFACTORY.

(CAN) METAL SLIVERS FOUND ON CHIP PLUG DURING DAILY INSPECTION. REMOVED FREEWHEEL UINT AND SEVERAL MORE SLIVERS WERE FOUND IN THE FREEWHEEL HSG. FREEWHEEL UNIT SENT TO MFG [S/N removed] CENTER FOR DISASSEMBLY AND INVESTIGATION. METAL SLIVERS WERE MAX .5" BY .005".

Parts most often named Actuator (37) · Support (4) · Bearing (4) · Pitch Link (4)

(CAN) DURING A SCHEDULED 100-HOUR INSPECTION TWO (2) VERTICAL CRACKS WERE FOUND ON A MAIN ROTOR PITCH LINK. THE CRACKS (APPROX. .180)

ACTUATOR FAILED AFTER FEBRUARY 2001 OVERHAUL. NO ALODINE OR OTHER CORROSION PROTECTION ON INSIDE OF CASE.INTERNAL CORROSION CAUSED FAILURE.

DURING THE ANNUAL INSPECTION, THE PIVOT SUPPORT ASSEMBLY WAS FOUND CORRODED. REPLACED SUPPORT ASSEMBLY WITH NEW PART. SUBMITTER RECOMMENDED SPRAYING A CORROSION PREVENTATIVE COMPOUND IN THE AREA OF THE SUPPORT ASSEMBLY. (X)

Parts most often named Starter Gen (14) · Starter (14) · Generator (4) · Bearing (4)

DURING NORMAL FLIGHT, THE PILOT REPORTED THE GENERATOR FAILED. THE HELICOPTER LANDED WITHOUT INCIDENT. SUBSEQUENT INVESTIGATION BY THE PILOT INDICATED THE STARTER GENERATOR WAS NOT TURNING WHEN THE ENGINE WAS ROTATED. UPON REMOVAL IT WAS VERIFIED THE STARTER GENERATOR DIREVE SHAFT HAD SHEARED AT THE DESIGNED SHEAR POINT.

(CAN) DURING ACFT INSPECTION, THE STARTER GENERATOR WAS FOUND TO HAVE EXCESSIVE PLAY IN THE SHAFT DAMPER. STARTER GENERATOR REPLACED. SHAFT WAS REMOVED FROM STARTER GENERATOR AND SPLINES WERE FOUND TO BE SEVERELY WORN.

(CAN) DURING 100/300 HR INSPECTION OF THE HELICOPTER THE STARTER GENERATOR FRICTION PADS WERE FOUND TO BE WORN. STARTER GENERATOR REPLACED.

Parts most often named Fcu (26) · Fuel Control (24) · Bearing (5) · Bypass Valve (1)

FIRST FUEL CONTROL UNABLE TO ADJUST START , SECOND FUEL CONTROL WAS UNABLE TO START AT ALL, REPLACED FUEL CONTROL DISCREPANCY WAS FIXED. THIS WAS ALL IN A YEARS TIME. ON AIRCRAFT 748 THE FUEL CONTROL WAS CHANGED DUE TO THE THROTTLE ARM WAS DIFFICULTY TO ROTATE. ON AIRCRAFT 774 THE FUEL CONTROL WAS CHANGED DUE TO STARTING ISSUES AND THE SECOND ONE WAS CHANGED DUE TO [tail no. removed] HUNTING. SO 5 FUEL CONTROLS WERE REPLACED WITHIN 2020 TOO 2021. NONE OF THE FUEL CONTROLS MADE IT TO THE REQUIRED 2500 OVERHAUL TIME.

THE AIRCRAFT SUFFERED AN INFLIGHT ENGINE OVERSPEED AND SUBSEQUENT ENGINE FAILURE. THE PILOT PERFORMED A SUCCESSFUL AUTOROTATION TO THE GROUND WITH NO DAMAGE TO THE AIRFRAME AND NO INJURIES TO THE OCCUPANTS. AFTER RECOVERY OF THE ACFT AND REMOVAL. INSPECTION OF THE ENGINE REVEALED THAT THE FCU SUFFERED A CATASTROPHIC DRIVE BEARING FAILURE WHICH WAS THE ROOT CAUSE OF THE ENGINE FAILURE.

(CAN) ENGINE UNCONTROLLED ACCELERATION OCCURRED DURING FLIGHT, CAUSING A MAIN ROTOR OVERSPEED TO 110 PERCENT. PILOT REDUCED THROTTLE TO MAINTAIN RPM WITHIN LIMITS AND LANDED. GROUND RUN SHOWED THE ENGINE CONTINUED TO ACCELERATE PAST IDLE DURING START SEQUENCE. FUEL CONTROL SENT FOR ANALYSIS WITH 55.6 HRS REMAINING.

Parts most often named Compressor (10) · Bearing (5) · Case (5) · Scroll (3)

(CAN) IT WAS REPORTED TO BELL: ENROUTE WITH A PASSENGER AND SUSTAINED A SUDDEN POWER LOSS. PILOT AUTOROTATED TO AN OPEN FIELD AND THE LANDING GEAR WAS DAMAGED DURING LANDING BUT AIRCRAFT REMAINED UPRIGHT. INVESTIGATION FOUND THE PC SAFETY VALVE HAD FAILED. NO INJURIES (TC# 20190110019)

(CAN) A ENGINEER WAS CALLED TO THE HELICOPTER DUE TO A DEFECT OF LACK OF POWER IN THE POWER ASSURANCE CHECK. THE ENGINEER CARRIED OUT A COMPRESSOR WASH STILL LACK OF POWER. THE ENGINEER REMOVED THE COMBUSTION CASE AND FOUND PART OF THE COMPRESSOR CASE HALF STATOR VANE IN THE TURBINE ASSY. THE HELICOPTER WAS GROUNDED. THE COMPRESSOR ASSY AND TURBINE ASSY WERE REPLACED DUE TO DAMAGE.

INITIATED A NORMAL TAKEOFF TO THE SOUTH FROM TB-45. APPROXIMATELY 3-5 SECONDS AFTER INITIATION, A LOUD BANG WAS HEARD WITH ACCOMPANING AIRFRAME SHUTTER. ABORTED TAKE OFF. SECOND BANG AND SHUTTER FOLLOWED AS ACFT SETTLED TO THE GROUND.