N701AL

ATA 7230

Part: BLADE — MISSING (IP ROTOR)

DURING TROUBLE SHOOTING FOR A REPORTED "WHINE" NOISE WHEN N1 IS ABOVE 71%, A FIELD BORESCOPE INSPECTION DISCOVERED A MISSING 3RD STAGE IP ROTOR BLADE. DISASSEMBLY OF THE ENGINE CONFIRMED THAT ONE OF THE 3RD STAGE IPC ROTOR BLADES WAS MISSING.

ATA 2697

Part: CONNECTOR — FAULTY (FIRE DETECTION)

ON PRE START, NR 1 ENGINE FIRE TEE HANDLE LIGHTS WOULD NOT TEST IN FORWARD POSITION. THE MECHANIC REMOVED AND REPLACED THE FAULTY CONNECTOR AND THE AIRCRAFT WAS RETURNED TO SERVICE AFTER OPERATIONAL CHECK OF THE SYSTEM. (K)

ATA 3260

Part: PROXIMITY SWITCH — OUT OF ADJ (MLG)

DURING TAKEOFF RT MAIN GEAR RETRACT UNSAFE LIGHTS. ADJUSTED UPLOCK PROXIMITY SWITCH ON RT MAIN GEAR, PERFORMED RETRACTION TEST. NO DEFECTS NOTED.

ATA 3212

Part: SWITCH — LOOSE (CYCLIC GRIP)

INADVERTANT FLOAT INFLATION DURING FINAL APPROACH TO OFFSHORE PLATFORM. FOUND COPILOT CYCLIC GRIP CRACKED AROUND FLOAT INFLATION SWITCH. SWITCH WAS LOOSE IN GRIP. WHEN SWITCH WAS MOVED, INFLATION RELAY WOULD ENERGIZE. SUBMITTER RECOMMENDS EXAMINATION OF GRIP ASSEMBLIES FOR SECURITY OF FLOAT INFLATION SWITCH. COMPONENT P/N 7645002010102.

ATA 7210

Part: FILTER CAP — FAILED (ENGINE OIL)

SHORTLY AFTER TAKEOFF FROM AN OFFSHORE PLATFORM IN THE GULF OF MEXICO, THE NR 1 ENGINE FIRE WARNING LIGHT ILLUMINATED AND THE NR 1 ENGINE OIL PRESSURE BEGAN TO FLUCTUATE. THE FLIGHT CREW SECURED THE NR 1 ENGINE AT WHICH TIME THE FIRE WARNING LIGHT EXTINGUISHED AND FLEW TO THE NEAREST AIRPORT AND EXECUTED A 'SINGLE ENGINE' RUN-ON LANDING. EXAMINATION OF THE ENGINE REVEALED THAT ONE OF THE ATTACHMENT EARS ON THE ENGINE'S INTERNAL OIL FILTER CAP HAD FRACTURED CAUSING THE ENGINE TO LOSE ALL OF THE OIL.

ATA 7210

Part: SCAVENGE BODY — WORN (SCAVENGE TUBE)

UPON DISASSEMBLY OF GEARBOX, REMOVED OIL PUMP ASSY. VISUALLY INSPECTED, SHOWED WEAR AT SCAVENGE BODY SURFACE, AND IN THE TUBE BONE. SCAVENGE TUBE WORN IN SCAVENGE BODY. SUSPECT CAUSE IS DUE TO IMPROPER FIT OR ALIGNMENT BRACKETS.

ATA 7321

Part: FUEL CONTROL — WATER CONTAM (NR 1 ENGINE)

DURING FLIGHT CHECK/HOVER, COMPRESSOR STALLED. REMOVED FROM ENGINE, INSPECTED PX-AIR CIRCUIT ON FUEL CONTROL, FOUND EXCESSIVE AMOUNT OF WATER.

ATA 6510

Part: TUBE ASSY — DEBONDED (T/R DRIVE)

DISASSEMBLY FOR OVERHAUL FOUND T/R DRIVE TUBE DEBONDED BEYOND MANUFACTURER'S MAXIMUM ALLOWABLE LIMITS.

ATA 6510

Part: OUTER HOUSING — CORRODED (T/R DRIVESHAFT)

DISASSEMBLY FOR OVERHAUL FOUND EXCESSIVE CORROSION ON MOUNT LUGS BEYOND MAXIMUM ALLOWABLE CLEAN-UP LIMITS.

ATA 7240

Part: COMBUSTION CASE — CRACKED (ARMPIT)

THIS DEFECT WAS DISCOVERED AT 1750-HOUR OVERHAUL. OUTER COMBUSTION CASE WAS CRACKED IN ARMPIT UNDER THE SCREEN PATCH REINFORCEMENT AND EXTENDED ON SEAM AND INTO THE SEAM PERPENDICULAR TO THE FLANGE AND PARALLEL TO THE FLANGE. A CRACK SUCH AS THIS MAY CAUSE POSSIBLE POWER LOSS IN ENGINE. NO REPAIR IS PERMITTED IN THIS AREA. OUTER COMBUSTION CASE IS SCRAPPED. CAUSE UNKNOWN.