Classic Helicopter Group, LLC

Part: ENGINE — FLAMED OUT (NR 1) · airframe 3,758 hrs · 14,015 cycles

DURING ENROUTE PHASE OF FLIGHT, ENGINE #1 FLAMED OUT. PILOT REPORTED FUEL PRESSURE CAUTION LIGHT ILLUMINATED. PILOT UTILIZED #2 ENGINE TO PERFORM A RUN ON LANDING SUCCESSFULLY WITH NO DAMAGE TO AIRCRAFT, NO INJURY TO PILOT OR PASSENGERS. AIRCRAFT HAS BEEN TRUCKED TO A LOCATION FOR FURTHER TROUBLESHOOTING. AS OF THIS REPORT, AIRCRAFT IS STILL OUT OF SERVICE FOR CONTINUED TROUBLESHOOTING OF ANOMALY. THIS EVENT OCCURRED NEAR THE SAN JUAN AIRPORT IN PUERTO RICO ON MAY 22, 2026.

Part: GREASE FITTING — DEFECTIVE (FLIGHT CONTROLS) · airframe 10,423 hrs · 5,316 cycles

GREASE FITTING ON MAIN ROTOR PITCH LINK UNIVERSAL BEARING WOULD NOT ACCEPT GREASE BUT WOULD PURGE GREASE. UPON FURTHER INVESTIGATION, THE FITTING APPEARS TO HAVE BEEN ASSEMBLED INCORRECTLY WITH THE STOPPER BALL ON THE INSIDE OF FITTING WITH THE SPRING PRESSING THE BALL TOWARDS BEARING, PREVENTING GREASE FROM FLOWING INTO BEARING, BUT ALLOWING GREASE TO FLOW OUT OF BEARING.

Part: DECK PLATE — CRACKED (ENGINE BAY) · airframe 885 hrs

CRACK IN THE BOTTOM ENGINE DECK WHERE THE AIR-CONDITIONING LINES COME THROUGH. REPAIR MADE WITH BELL DATA.

Part: SKIN — CORRODED (ZONE 100) · airframe 15,027 hrs · 6,119 cycles

FOUND CORROSION ON THE LOWER LEFT FORWARD FUSELAGE WHILE AIRCRAFT WAS IN THE SHOP FOR HEAVY MAINTENANCE. AREA WAS REPAIRED BY ARROW AVIATION REPAIR STATION #Y3AR527Y UNDER W/O #23-339. REPAIR SCHEME, AE-100-1 #23RL-015, WAS PROVIDED BY THE MANUFACTURER BELL HELICOPTER TEXTRON.

Part: BRACKET — CRACKED (MR BRAKE)

DURING 3600 HOUR OVERHAUL FOUND BRAKE CALIPER MOUNTING BRACKET CRACKED, STARING AT LOWER CENTER CORNER EXTENDING AROUND BOLT HOLE ON BOTH SIDES. NO OBVIOUS SIGNS OF WHAT STRESSES CAUSED THE CRACK, NOR ANY INDICATION OF AN INDECENT.

Part: BRACKET — CRACKED (MR BRAKE)

DURING 3600 HOUR OVERHAUL FOUND BRAKE CALIPER MOUNTING BRACKET CRACKED, STARING AT LOWER CENTER CORNER EXTENDING AROUND BOLT HOLE ON BOTH SIDES. NO OBVIOUS SIGNS OF WHAT STRESSES CAUSED THE CRACK, NOR ANY INDICATION OF AN INDECENT.

Part: LINE — LEAKING (HYDRAULIC SYS) · airframe 5,426 hrs · 35,422 cycles

PILOT AND MECHANIC NOTICED LOSS OF HYD FLUID WHEN ACFT LANDED. FOUND DEFECTIVE HOSE.

Part: LINE — LEAKING (HYD SYSTEM) · airframe 5,404 hrs · 35,287 cycles

DEFECTIVE HYD HOSE = MECHANIC NOTICED EXCESSIVE AMOUNT OF HYD FLUID.

Part: HOSE — LEAKING (HYD SYSTEM) · airframe 5,400 hrs · 35,256 cycles

DEFECTIVE HYDRAULIC HOSE.

Part: LINE — LEAKING (HYDRAULIC SYS) · airframe 5,384 hrs · 35,028 cycles

PILOT LANDED AND LET PASSENGERS OFF AND NOTICE ALOT OF FLUID, MAINTENANCE WAS CALLED TO SITE AND DISCOVERED FLUID COMING OUT OF HOSE FITTING. FOUND DEFECTIVE HYDRAULIC HOSE.

Part: LINE — LEAKING (HYDRAULIC SYS) · airframe 5,346 hrs · 34,772 cycles

DEFECTIVE HYD HOSE - AFTER 5.2 HRS TIME INSERVICE - PILOT LANDED, WHILE LETTING PASSENGERS OFF, NOTICED ALOT OF FLUID - MX WENT TO SITE AND DISCOVERED FLUID COMING OUT OF FITTING OF HOSE.

Part: LINE — LEAKING (HYDRAULIC SYS) · airframe 5,308 hrs · 35,425 cycles

DEFECTIVE HUD HOSE, INSTALLED NEW TYPE HOSE AND AFTER 44.0 HOURS - IT STARTED LEAKING WHERE HOSE GOES INTO FITTING.

Part: TUBE — TORN (T/R CONTROL) · airframe 7,758 hrs

DURING ROUTINE INSPECTION OF TAILBOOM, DISCOVERED TORN WEAR SLEEVES ON TAIL ROTOR CONTROL TUBE. THE TAIL ROTOR CONTROL TUBE WAS INSTALLED NEW 13.0 PRECEDING THIS DISCOVERY. WEAR SLEEVES ARE PART OF THE CONTROL TUBE ASSY. THE TEARING WAS A RESULT OF CONTACT WITH (BULKHEAD) BEARINGS, PN 350A27-1190-20. DURING REPLACEMENT OF THE TAIL ROTOR CONTROL TUBE, 5 EA NEW BEARINGS WERE ALSO INSTALLED. SUBMITTING A SECOND SDR FOR FAULT DISCOVERED IN BULKHEAD BEARINGS.

Part: INDICATOR — DAMAGED (NG) · airframe 4,063 hrs · 16,493 cycles

NG INDICATOR DIGITAL READOUT IS DIFFICULT TO READ IN DAYLIGHT CONDITIONS.

Part: BOOT — TORN (SWASHPLATE) · airframe 4,058 hrs · 16,474 cycles

MAST BOOT CAME FREE FROM ROTATING SWASH PLATE. A PIECE OF THE BOOT LOWER FLANGE TORE OFF AND DEPARTED THE ACFT MOST LIKELY HITTING THE P/C LINKS THAT CAUSED A VIBRATION FELT IN THE CYCLIC CONTROL STICK.

Part: WARNING LIGHT — ILLUMINATED (CHIP DETECTOR) · airframe 3,903 hrs · 15,911 cycles

ENGINE CHIP LIGHT ILLUMINATED DURING FLIGHT. AFTER LANDING, TECH FOLLOWED ALL PROCEDURES IN THE MM.

Part: CONTROL CABLE — SEVERED (PWR CONTR) · airframe 5,523 hrs · 13,472 cycles

AFTER LANDING DURING EMS MISSION, PILOT REPORTED ACFT WAS UNABLE TO SHUTDOWN WITH TWIST GRIP ON COLLECTIVE. MX ARRIVED, CONFIRMED LINKAGES CONNECTED CORRECTLY TO BOTH ENDS-AFTER REMOVAL, FLAT WIRE THAT MOVES INSIDE THE HSG WAS FOUND SEVERED ABOUT 4 FT AFT FROM TWIST GRIP.

Part: SKIN — CRACKED (TAILBOOM) · airframe 3,842 hrs · 15,695 cycles

FOUND CRACK ON UPPER RIGHT SKIN OF HORIZONTAL STABILIZER DURING INSPECTION. HORIZONTAL STABILIZER WILL BE REPLACED/REPAIRED.

Part: BEARING — WORN (M/R HEAD) · airframe 4,124 hrs · 6,409 cycles

PILOT REPORTED M/R VIBRATION. FOUND BEARING WORN IN MAIN ROTOR HEAD.

Part: DRAIN VALVE — STUCK (FUEL SYS)

PRIOR TO FIRST FLIGHT OF THE DAY, THE PILOT SUMPED THE FUEL FILTER. ON FIRST START OF THE DAY PILOT DISENGAGED FUEL BOOST PUMP (ACCORDING TO PROCEDURES), THE ENGINE FLAMED OUT. UPON INVESTIGATION, THE AIRFRAME FUEL FILTER KIT PN 350-600024 DRAIN VALVE WAS PARTIALLY STUCK OPEN, SUSPECT AIR HAD GOTTEN INTO THE FUEL SYSTEM. UPON FURTHER INVESTIGATION FUND DEBRIS IN THE FUEL FILTER BOWL. PROCEDURES FOR INSPECTION TO BE PERFORMED BEFORE FIRST FLIGHT ARE IN THE MAINTENANCE ICA DOCUMENT ICA-ECL-129, BUT THEY ARE NOT INCORPORATED INTO THE FLIGHT MANUAL SUPPLEMENT, THEREFORE THE PILOT WAS UNAWARE OF THE PROCEDURES TO BE INCLUDED IN BFF INSPECTIONS THAT ARE REQUIRED. (K)

Part: CARBON SEAL — LEAKING (FREEWHEEL UNIT)

CARBON SEAL LEAKING. REPLACED WITH NEW SEAL FROM BELL HELICOPTER.

Part: DISC PAC — OUT OF LIMITS (TAIL ROTOR)

TAIL ROTOR DISC PACKS OUT OF LIMITS. REPLACED WITH NEW DISC PACS FROM BELL HELICOPTER.

Part: SWITCH — DEFECTIVE (LT MLG)

LEFT MAIN GEAR INDICATED DOWN AFTER SECOND RECYCLE. LIGHT REMAINED ON FOR DURATION OF FLIGHT. REPLACED LEFT MAIN LANDING GEAR DOWN LOCK SWITCH. OPS CHECKED GOOD IAW YS-11 MM 32-61-6.

Part: INDICATOR — MALFUNCTION (FUEL QUANTITY)

FUEL QUANTITY INDICATOR STAYS IN TEST MODE FOR LONG PERIODS OF TIME. REPLACED WITH NEW INDICATOR.

Part: LINKAGE — NOT CONNECTED (RT ENGINE)

RIGHT ENGINE HIGH STOP LIGHT ILLUMINATED IN FLIGHT AT APPROXIMATELY 5,000 FEET, 230 KNOTS AND 20 DEGREES CELSIUS. FOUND HIGH STOP LINKAGE UNDONE. RE-CONNECTED LINKAGE. GROUND OPS CHECKED GOOD.

Part: PULLEY — WARPED (AIR CONDITIONER)

UNDEFINED SMOKE ODOR IN THE COCKPIT DURING LAST PORTION OF CLIMB TO 10,000 FEET. GRADUALLY WENT AWAY AFTER TEN MINUTES. UNABLE TO IDENTIFY OR ISOLATE SOURCE. FOUND AIR CONDITIONING DRIVE PULLEY WARPED AND CORRODED CAUSING DRIVE BELT TO BURN IN A SHORT PERIOD OF TIME. REPLACED JACK SHAFT AND PULLEY.

Part: DE-ICE — MALFUNCTIONED (RT WINDSHIELD)

WINDSHIELD DE-ICE GREEN LIGHTS DID NOT COME ON IN LOW, THE RIGHT LIGHT COMES ON. LATER IN FLIGHT, CYCLED ON AND OFF. POSSIBLE ASSOCIATED INTERMITTENT SMOKE ODOR. RAN AIRCRAFT AT ILN, OPERATED WINDSHIELD DE-ICE FOR ABOUT FIVE MINUTES. SYSTEM OPS CHECKED GOOD IAW YS-11 MM, NO SMOKE OR ODOR NOTED.

Part: OIL COOLER — CRACKED (NR 1 ENGINE)

NR 1 ENGINE INFLIGHT SHUTDOWN DUE TO LOW OIL PRESSURE, 6 TO 10 PSI. MAINTENANCE FOUND THE NR 1 OIL COOLER LEAKING, CRACKED. REPLACED OIL COOLER IAW ROLLS ROYCE MM 79-20-1. REPLACED NR 1 ENGINE IAW ABX WORK CARD 7202. OPS AND LEAK CHECKED GOOD.

Part: INVERTER — DEFECTIVE (NR 1)

SMOKE IN COCKPIT, EITHER NR 1 INVERTER OR AIR CONDITIONER. REPLACED NR 1 INVERTER IAW YS-11 MM CHAPTER 24. OPS CHECKED GOOD, NO SMOKE NOTED.