R22Beta · Beta II · Mariner

Parts most often named V-Belt (41) · Actuator (28) · Sheave (10) · Belt (6)

PILOTS FOUND A TEAR IN ONE OF THE DRIVE V-BELTS. UPON INSPECTION OF THE CLUTCH ASSEMBLY, THE UPPER SHEAVE HAD A SHARP STEP WORN INTO IT. AFTER DISASSEMBLY OF THE SPRAG CLUTCH DAMAGE WAS FOUND ON THE CLUTCH AND ONE OF THE CLUTCH SHAFT BEARINGS.

CUSTOMER REPORTED ACTUATOR ASSEMBLY P/N: A051-1 DOES NOT RETRACT WHEN SWITCH IS TURNED TO THE OFF POSITION AFTER FLIGHT.

CUSTOMER SENT IN ACTUATOR ASSEMBLY A051-1 FOR WARRANTY. COLUMN SPRINGS WERE FOUND TO BE NOT ENGAGING OR DISENGAGING SIMULTANEOUSLY WHEN BENCH TESTED.

Parts most often named Belt (20) · Drive Belt (10) · Actuator (4) · Clutch (4)

(CAN) CLUTCH ACTUATOR WOULD NOT DISENGAGE. MULTIPLE INTERMITTENT FAILURES OF CLUTCH ACTUATOR OCCURRED BEFORE UNIT WAS REPLACE. ON REMOVAL CLUTCH ACTUATOR WIRES WERE FOUND TO BE BADLY CHAFED. AT THE TIME OF CLUTCH ACTUATOR REPLACEMENT, DRIVE BELTS WERE FOUND TO BE STRETCHED BEYOND LIMITS AND REPLACED.

THE PILOT REPORTED A CLUTCH LIGHT COMING ON FOR MORE THAN 5 SECONDS, FOLLOWED THE PROCEDURES IN THE POH AND MADE A PRECAUTIONARY LANDING. UPON VISUAL INSP IT WAS DEFECTED THAT ONE OF THE DRIVE BELTS IN THE CLUTCH SYS HAD FAILED AND CAUSED THE CLUTCH ACTUATOR TO ENGAGE CAUSING THE CLUTCH LIGHT TO ILLUMINATE. THERE WERE NO DAMAGES TO THE ROTORCRAFT OR ANY INJURIES TO THE PILOTS. DRIVE BELTS WHERE REPLACED AND THE ROTORCRAFT WAS RETURNED TO [S/N removed].

(CAN) BELTS WERE REPLACED AT 2200HR OVERHAUL AND AFTER 38 HRS IN [S/N removed] WERE FOUND SEPARATED IN A SECTION ABOUT 2 INCHES LONG. (TC NR 20070615002)

Parts most often named Bearing (28) · Blade (6) · Boot (2) · Spindle (2)

PILOTS REPORTED VIBRATIONS IN THE CYCLIC, UPON INSPECTION IT WAS FOUND THAT ONE OF THE MAIN ROTOR BLADES HAD BRINELLED SPINDLE BEARINGS

PILOTS REPORTED VIBRATIONS IN THE CYCLIC CONTROLS, UPON INSPECTION IT WAS FOUND THAT ONE SET OF SPINDLE BEARINGS ON ONE MAIN ROTOR BLADE WERE FOUND TO BE BRINELLED. THE BEARINGS ON THIS SPECIFIC SPINDLE HAVE BEEN REPLACED SEVERAL TIMES BEFORE.

PILOTS REPORTED VIBRATIONS IN THE CYCLIC CONTROL. INSPECTION OF THE MAIN ROTOR BLADE SPINDLE BEARINGS SHOWED BRINELLED BEARINGS ON BOTH MAIN ROTOR BLADE SPINDLES.

Parts most often named Magneto (7) · Bearing (6) · Gear (6) · Distributor Blk (4)

PILOTS EXPERIENCED ENGINE ROUGHNESS IN AIR. UPON LANDING, MAINTENANCE FOUND MAGNETO WAS DIFFICULT TO SPIN AND CLUNKY IN IT'S ROTATION, INDICITIVE OF BEARING FAILURE.

MAGNETO COIL HIGH TENSION TAB WAS BENT TOO FAR UPWARDS DURING MANUFACTURING, TO THE POINT THAT THE TAB WAS CONTACTING THE DISTRIBUTOR BLOCK GEAR. AS A RESULT, A LARGE DIVOT WAS WORN INTO THE COIL TAB DUE TO THE ROTATION OF THE GEAR CONTACTING THE COIL TAB DURING IT'S ROTATION.

COIL TAB WAS BENT TOO FAR UP DURING MANUFACTURING INSTALLATION, WHICH CAUSED A DEEP ANGULAR DIVOT TO BE WORN IN THE COIL TAB BY THE DISTRIBUTOR BLOCK GEAR SINCE IT WAS NOT FLAT AGAINST THE GEAR. MAGNETO HAD NOT BEEN OPENED SINCE NEW AND THIS DAMAGE WAS DISCOVERED AT THE 500HR HOUR INTERNAL MAGNETO INSPECTION.

Parts most often named Gearbox (7) · Fanwheel (7) · Transmission (3) · Bearing (2)

PILOT REPORTED 2 PER VIBRATION. INSPECTION FOUND RUBBER SURROUNDING STEEL BUSHING ON ONE OF FOUR MAIN GEAR BOX MOUNTS HAD FAILED ALLOWING EXCESS MOVEMENT OF MAIN ROTOR DRIVE SYSTEM.

MAIN ROTOR GEARBOX INPUT SEAL LEAKING WITH 181.3 TSN. PREVIOUS INPUT SEAL REPLACED FOR LEAK WITH 391.3 TSN. PRIOR TO THIS INPUT SEAL REPLACED FOR LEAK WITH 46.6 TSN.

PILOT REPORTED VIBRATION, BURNING RUBBER ODOR AND LOSS OF ROTOR RPM WHILE IN CRUISE FLIGHT, DURING DOWNWIND PORTION OF TRAFFIC PATTERN PRACTICE. PILOT ENTERED AUTOROTATION AND PERFORMED SUCCESSFUL AUTOROTATION AND POWER OFF LANDING. UPON EXAMINATION OF ACFT ON SCENE, THE FAN SHAFT WAS OBSERVED TO BE BROKEN AND SEPARATED JUST FORWARD OF THE LOWER ACTUATOR BEARING. AFFECTED PARTS WERE REMOVED AND RETAINED BY THE FAA FOR EXAMINATION BY THE MFG.

Parts most often named Tachometer (13) · Dual Tachometer (7) · Warning Unit (4) · None (3)

CUSTOMER REPORTED DUAL TACHOMETER P/N: A792-4 ROTOR NEEDLE WAS JUMPING AROUND (NIL TSOH). FURTHER INSPECTION REVEALED SCREW BACKED OUT OF INTERNAL PLATE.

Parts most often named Fanwheel (6) · Bearing (3) · Hub (2) · None (1)

THE ENGINE COOLING FAN WHEEL WAS REMOVED TO FACILITATE OTHER MAINTENANCE AND A CRACK WAS FOUND ON THE FAN AT A BALANCE BOLT HOLE.

A POST FLIGHT INSPECTION OF THE DRIVE SYSTEM WAS PERFORMED AFTER ENCOUNTERING A FLICKERING CLUTCH LIGHT. DURING THE INSPECTION, THE FANWHEEL HUB ATTACHING HARDWARE WAS FOUND FRETTING AND LOOSE.

DURING THE REPLACEMENT OF THE CRANKSHAFT SEAL THE AIRCRAFT FANWHEEL WAS REMOVED AND THE MOUNTING HUB WAS FOUND CRACKED. IN ADDITION, THE FANSHAFT WAS GOUGED FROM THE CRACK IN THE FANWHEEL MATING SURFACE. BOTH COMPONENTS WERE REPLACED. THE CAUSE OF THE CRACK IS UNKNOWN.

Parts most often named Pushrod (7) · Cylinder (3) · Rocker (2) · Retainer (2)

THIS IS THE FOURTH FACTORY NEW AIRCRAFT WE HAVE RECEIVED IN A ROW FROM ROBINSON HELICOPTER CO WITH THIS ISSUE. ALL PUSHRODS AND ROCKER ARMS WERE FOUND TO BE SORED AT THE MATING SURFACE. PARTS HAVE SINCE BEEN SENT TO RHC AND WE ARE WAITING FOR REPLACEMENT PARTS. WE BELIEVE THAT THIS IS CAUSED BY A LACK OF LUBRICATION AT THIS MATING SURFACE DURING INITIAL RUN UPS OR THE DE-PICKLING PROCESS.

DURING ROUTINE MX, LYCOMING SB388C (EXHAUST VALVE GUIDE INSPECTION) FOUND 3 OF 4 EXHAUST ROCKER ARMS, PUSH RODS & LIFTER SOCKETS TO HAVE MECHANICAL DAMAGE "HEAVY SCUFF". LYCOMING FACTORY OVERHAULED, O-360-J2A, [S/N removed], ETT: 667.2, ETSO: 330.6

CYLINDER 4 ROCKER SHAFT BOSS ON EXHAUST SIDE BROKE OFF THE CYLINDER HEAD & WAS BOUNCING AROUND IN THE ROCKER BOX LEAVING A PORTION OF THE ROCKER SHAFT UNSUPPORTED DURING OPERATION. THE POINT OF FAILURE IS UNKNOWN. WHAT IS KNOWN IS THAT THE CYLINDER TOP END FAILED WITHIN 135.6 HOURS IN [S/N removed]! THE FAILED BOSS WAS FOUND WHILE PERFORMING SB388C AT THE FIRST 100HR INSPECTION POST ACFT OVERHAUL.

Parts most often named Gearbox (9) · None (2) · Seal (2) · Chip Detector (1)

CUSTOMER REPORTED TAIL ROTOR GEARBOX ASSEMBLY P/N: B021-1 EXPERIENCE METAL CONTAMINATION. NOTE: CORRECTED UNIQUE CONTROL #YV3R2022052600528.

DURING 500 HOUR TAIL ROTOR GEARBOX FLUSH PRODEDURE, FOUND PLASTIC FALLING OUT OF CHIP DETECTOR/DRAIN WHEN REMOVED FROM GEARBOX. THIS PROBLEM CAUSES CHIP DETECTOR TO MAKE AN ELECTRICAL SHORT AND MAY SEEP OIL, BECOMES UNUSABLE.

(CAN) DURING GROUND RUN, PILOT REPORTED T/R CHIP LIGHT. T/R GEARBOX OIL DRAINED AND CHIP DETECTOR INSPECTED. FOUND LARGE QTY OF FERROUS METAL FLAKES ON DETECTOR. T/R GEARBOX REMOVED FROM [S/N removed] AND SENT TO MFG FOR REPAIR.

Parts most often named Bearing (10) · Hub (1) · Bearings (1) · Yoke (1)

PILOTS EXPERIENCED ERRATIC CYCLIC MOVEMENT. UPON INSPECTION IT WAS FOUND THAT THE SPINDLE BEARINGS IN ONE MAIN ROTOR BLADE WERE BRINELLED.

IN FLIGHT VIBRATION REPORTED. FOUND SPINDLE BEARINGS BRINELLED. NO OVER SPEEDS REPORTED. SPINDLE & BEARING ASSEMBLIES P/N A158-3, [S/N removed] & [S/N removed] REMOVED FROM MRBS P/N A016-6, [S/N removed] & [S/N removed]. MRBS & SPINDLES TSN: 342.3

PILOT REPORTED VIBRATIONS IN THE CYCLIC DURING AUTO ROTATIONS. THE MAIN ROTOR SPINDLE BEARINGS WERE INSPECTED AND FOUND TO BE BRINELLED. THE SPINDLE BEARINGS WERE REPLACED 34.5 HOURS PRIOR TO THIS EVENT. SEE SDR UNIQUE CONTROL #8HBR20220730046