NOVICTOR AVIATION LLC

Operated by Novictor Aviation LLC — Commuter air carrier (135) Operator Does Business As: Rainbow Helicopters (per NTSB report)

A failure of the flex plate yoke flange assembly due to incorrectly torqued bolts. Contributing was the maintenance personnel’s inadequate inspection of the tail rotor flex plate assembly.

Operated by Novictor Aviation — On-demand air taxi (135), Commercial air tour (136) Operator Does Business As: (per NTSB report)

The instructor pilot’s inadequate supervision of the pilot receiving instruction, which resulted in a hard landing, and substantial damage to the tail boom.

Operated by Novictor Aviation LLC (per NTSB report)

The helicopter’s encounter with a strong downdraft or outflow boundary while operating at a higher than recommended airspeed in turbulence which resulted in a low-G condition, excessive main rotor flapping, and an in-flight breakup when the main rotor contacted the cabin area.

Operated by Novictor Aviation (per NTSB report)

The pilot’s sudden incapacitation from an undiagnosed heart condition during flight, which resulted in a hard landing.

Operated by Novictor Aviation (per NTSB report)

Loss of oil in flight as a result of a loose oil filter adapter which resulted in the pilot initiating an immediate landing to an open field. Contributing to the accident was the pilot's manipulation of the throttle that led to a reduction in rotor rpm, which resulted in his inability to perform a normal landing.

Part: PUMP — INOPERATIVE (ZONE 100) · airframe 3,137 hrs

LOW FUEL PRESSURE LIGHT ILLUMINATED IN FLIGHT. NO ENGINE ROUGHNESS. VERIFIED ELECTRICAL FUEL PUMP NOT RUNNING. REPLACED ASSY PN D743-3 ASSY PER MM. THIS IS A COMMON ISSUE WITH THE R44 RAVEN II.

Part: BEARING — SLIPPED (HYD SYS) · airframe 17,311 hrs · 69,333 cycles

DETECTED NON CONFORMITY ON HYDRAULIC DRIVE BEARING PULLEY. DISCOVERED FRETTING DUST AROUND HYDRAULIC DRIVE PULLEY. FURTHER INVESTIGATION REVEALED PULLEY PN 350A35109224 HAVING SLIPPED ON INNER RACE OF DRIVE BEARING MFG PN 593733.

Part: YOKE — FAILED INSP (MAIN ROTOR) · airframe 1,699 hrs

LOSS OF MR RPM INDICATION DURING RUN UP. SUBSEQUENT VISUAL INSPECTION OF HALL EFFECT SENDERS REVEALED NON CONFORMITY OF C908-1 REV K YOKE. DISASSEMBLY REVEALED FULL TORQUE ON ALL FASTENERS, BUT WEAR ON SPLINES OF YOKE AND PINION. ALL INFO SENT TO ROBINSON HELICOPTER COMPANY TECHNICAL SUPPORT FOR EVALUATION. ASSEMBLY HAD 500 HOURS IN SERVICE.

Part: CONTROL ROD — DEFORMED (TAIL ROTOR) · airframe 4,737 hrs

DURING ATTEMPTED ROTOR ENGAGEMENT FOLLOWING ENGINE START, TAIL ROTOR PEDALS DEFLECTED FULL LEFT. ENGINE WAS IMMEDIATELY SHUT DOWN AFTER LESS THAN 45 DEGREES OF ROTOR MOVEMENT. INSPECTION REVEALED CONTACT BETWEEN AFT FLEX PLATE AND TAIL ROTOR CONTROL ROD. FURTHER INSPECTION AND ROOT CAUSE PENDING.

Part: INTAKE VALVE — FAILED (NR 6 CYLINDER) · airframe 1,874 hrs

ABOUT 30 MINUTES INTO A TOUR, PILOT HEARD A SOUND AND EXPERIENCED LOSS OF POWER AND HIGH MANIFOLD PRESSURE. INITIATED POWER ON LANDING ON AN ADJACENT OPEN FIELD. VISUAL INSPECTION REVEALED OIL LEAK NEAR CYLINDER # 6. UPON REMOVAL OF VALVE COVER A BROKEN OFF VALVE STEM TIP WAS IDENTIFIED. NEW STYLE ROTATOR CUP INTAKE VALVE PN 17A29467 INSTALLED.

Part: INTAKE VALVE — DAMAGED (ENGINE) · airframe 1,470 hrs

PILOT IDENTIFIED HIGH MANIFOLD PRESSURE REQUIRED AFTER TAKE OFF AND PERFORMED A PRE CAUTIONARY LANDING OFF AIRPORT. INSPECTION REVEALED A WET SPARK PLUG ON CYLINDER # 6. AFTER REMOVAL OF THE VALVE COVER, A BROKEN INTAKE VALVE TIP WAS DISCOVERED. NEW STYLE ROTATOR CAP INTAKE VALVES ARE INSTALLED PER LYCOMING SI1280D.

Part: TAIL BOOM — DENTED · airframe 15,298 hrs · 41,866 cycles

FOLLOWING A ROUTINE TRAINING FLIGHT, DENTS WERE NOTED AT THE FORWARD END OF THE TAIL BOOM. THE TRAINING FLIGHT INCLUDED HOVERING AUTOROTATIONS WHICH WERE NOT RECEIVED OUT OF THE ORDINARY. CONTACTED OEM FOR INPUT.

Part: WINDOW — DEPARTED (PAX CABIN) · airframe 14,185 hrs · 65,177 cycles

SMALL LOWER PASSENGER DOOR WINDOW SEPARATED FROM FRAME AND DEPARTED THE AIRCRAFT. THE SMALL COMFORT WINDOW IS LARGER THEN THE OPENING AND IS INSTALLED FROM THE INSIDE. IT SHOULD NOT BE POSSIBLE TO COME LOSE TOWARD THE OUTSIDE OF THE AIRCRAFT. SUSPECT WRONG PART USED BY PREVIOUS OWNER. SIZE ISSUE WAS NOT EVIDENT DURING PERIODIC INSPECTIONS.

Part: WINDOW — DISLODGED (LT PAX CABIN) · airframe 14,185 hrs · 65,177 cycles

SMALL LOWER LEFT PASSENGER DOOR WINDOW BECAME DISLODGED FROM THE WINDOW FRAME. WINDOW SEPARATED FROM DOOR. THE WINDOW IS LARGER THEN THE OPENING AND IS INSTALLED FROM THE INSIDE. IT SHOULD BE IMPOSSIBLE FOR THE WINDOW TO SEPARATE. SUSPECT WRONG PART INSTALLED BY PREVIOUS OWNER.

Part: SPAR — CRACKED (TAIL ROTOR) · airframe 14,017 hrs · 64,973 cycles

PILOT REPORTED NOISE FROM TAIL ROTOR DURING ROUTINE PREFLIGHT CHECK. REMOVAL AND INSPECTION OF TAIL ROTOR ASSEMBLY REVEALED A SPLINTERED SPAR OUTSIDE OF ALLOWABLE CRITERIA. COMPONENT HAD REACHED 94% OF ITS LIFE LIMIT. REPLACED WITH NEW PART.

Part: STARTER GEN — POWER LOSS (ZONE 200) · airframe 14,313 hrs · 40,540 cycles

FOLLOWING PILOT REPORT OF LOSS OF ELECTRICAL POWER, FOUND AIRCRAFT BATTERY WITH 21.9 VOLTS. RG355 BATTERY SUBSEQUENTLY TESTED FOLLOWING CHARGE AT 129% CAPACITY. BATTERY TOTAL TIME 4 MONTHS & 400 HOURS. REPLACED STARTER GENERATOR FOR BENCH TESTING. NO DISCREPANCIES NOTED ON ELECTRICAL SYSTEM. STARTER GENERATOR HAD NO SIGNS OF HEAT OR DUST OR SMELL AND ROTATED SMOOTHLY. TEST RESULTS PENDING.

Part: INTAKE VALVE — BURNED (ENGINE)

DURING FLIGHT, PILOT EXPERIENCED "TORQUE KICK". PILOT MADE PRECAUTIONARY LANDING. INSPECTION REVEALED A BURNED INTAKE VALVE. ABOUT 3/8" OF THE MATING FACE WAS BURNED. AIRCRAFT IS NEW, ENGINE ONLY HAD ABOUT 200 HOURS ON IT.