N170MC

Part: INDICATOR — DAMAGED · airframe 8,874 hrs · 40,623 cycles

DME UNREADABLE. CO-PILOTS MASTER CAUTION LIGHT BARELY VISIBLE WHEN LIT. DH LIGHT ON RADAR ALTIMETER IS INTERMITTENT AND BARELY VISIBLE WHEN LIT. MAST MOMENT WARNING LIGHT BARELY VISIBLE WHEN LIT AND THE COLOR OF THE LIGHT HAS BEEN CHANGED FROM "RED" TO "GREEN". MASTER CAUTION PANEL LETTERING ON TWO "RED" WARNING LIGHTS LOCATED AT THE TOP CENTER OF THE PANEL ARE UNREADABLE.

Part: GUIDE — WORN (RT SLIDING DOOR) · airframe 8,483 hrs · 38,429 cycles

DURING FLIGHT, A CREWMEMBER NOTICED A GAP ON THE LOWER EDGE OF THE RT SLIDING DOOR. AN UNSCHEDULED LANDING WAS PERFORMED & THE DOOR WAS SECURED. FLIGHT CONTINUED WITHOUT ANY FURTHER INCIDENT. MX REPLACED A WORN GUIDE PN 117-24273-2 & WORN CATCHER PN 117-24281-12 ON THE LOWER RT SLIDING DOOR.

Part: SKIN — CRACKED (TAILBOOM) · airframe 8,304 hrs · 37,470 cycles

DURING A DAILY INSPECTION, A 2.5" LONG CRACK WAS DISCOVERED ON THE LT TAILBOOM SKIN STARTING AT THE FORWARD END OF THE OPENING FOR THE HORIZONTAL STABILIZER. CRACK WAS STOP DRILLED AND A REPAIR SCHEME REQUEST HAS BEEN SUBMITTED FROM THE MANUFACTURE FOR REPAIR.

Part: BLADE — DEBONDED (MAIN ROTOR) · airframe 8,273 hrs · 37,284 cycles

DURING FLIGHT, A NOISE WAS HEARD IN THE MAIN ROTOR SYS, FOLLOWED BY A VIBRATION THAT INCREASED. A PRECAUTIONARY LANDING WAS PERFORMED. FOUND EROSION TAPE HAD SEPARATED FROM NR1 MAIN ROTOR BLADE. WHEN THE TAPE SEPARATED, IT ALSO PULLED UP SOME FILLER MATERIAL FROM THE TOP SURFACE OF THE BLADE.

Part: DRIVE SHAFT — DAMAGED (TAIL ROTOR)

FOUND DURING INSPECTION, THE FORWARD TAIL ROTOR DRIVESHAFT WAS FOUND TO HAVE A DEEP GROOVE WORN INTO THE TUBE NEAR THE END OF THE SHAFT EXCEEDING THE MECHANICAL DAMAGE LIMITS. DAMAGE WAS CAUSED BY LOOSE REINFORCING WIRE FROM A NEARBY SCAT TUBE FOR THE AIR CONDITIONING DUCT. THE DUCT HAD SEPARATED EXPOSING THE WIRE.

Part: GYRO — FAILED (COCKPIT)

ATTITUDE GYRO WILL NOT CAGE. TECHNICIAN STATED UNIT ONLY WORKED FOR ONE WEEK AFTER INSTALLATION. REMOVED AND REPLACED. (X)

Part: BLADE — DEBONDED (MAIN ROTOR)

LEADING EDGEOF MAIN ROTOR BLADE DEBONDING (INBOARD JOINT). 193.4 HOURS SINCE REPAIR/OVERHAUL. REMOVED AND REPLACED. (X)

Part: INDICATOR — MALFUNCTIONED (TRIPLE TACH)

TACHOMETER'S NR 1 AND NR 2 NEEDLE SPLIT 2 PERCENT. REMOVED AND REPLACED.

Part: PICKUP — FAILED (ENGINE NG)

NG PICKUP INOPERATIVE. REPLACED NG PICKUP.

Part: BLADE — DEBONDED (T/R)

TAIL ROTOR BLADE DEBONDING. REMOVED AND REPLACED.

Part: CONTROL — SMOKES (LIGHTS)

LIGHT CONTROL UNIT SMOKES WHEN TURNED ON. CIRCUIT BREAKER TRIPS.

Part: PUMP — INTERMITTENT (FUEL)

PUMP INTERMITTENT WHEN A/C RUNNING. ZERO TIME SINCE OVERHAUL.

Part: CONTROL UNIT — MALFUNCTION (COCKPIT)

LIGHTS WILL NOT TURN 'ON'. NO OUTPUT VOLTAGE. INSTALLED ONLY 4.5 HRS BEFORE FAILURE. LOOSE PARTS INSIDE UNIT.

Part: MANIFOLD — LEAKS (ENGINE FUEL)

SUBMITTER STATES EXCESSIVE FUEL MANIFOLD LEAKS OVER THE LAST 18 MONTHS. ALLIED SIGNAL IS IN THE PROCESS OF RELEASING AN ASB LIMITING THE LIFE OF THE FUEL MANIFOLD TUBES. OTHER OPERATORS SUBMITTER CONTACTED ARE HAVING THE SAME PROBLEMS. OMNIFLIGHT HAS GONE TO A POST-FLIGHT CHECK AND A SHIFT-CHANGE CHECK OF THIS MANIFOLD.

Part: TRANSCEIVER — POT MISSING (SIDE TONE)

RECEIVED THIS UNIT WITH SIDE TONE ADJ. POT MISSING FROM AUDIO BOARD. INSTALLED AUDIO SIDE TONE MISSING POT, BENCH ALIGN AND CHECK. REMOVED AND REPLACED.

Part: TRANSCEIVER — DEFECTIVE (CONTROL HEAD)

ON INSTALLATION IN A/C, CONTROL HEAD GUARD INDICATOR LIGHT ILLUMINATED AND STAYED LIT EVEN WITH NO GUARD MODULE INSTALLED. REMOVED AND REPLACED.

Part: INDICATOR — FLUCTUATES (TRIPLE TACH N2)

NR 1 N2 NEEDLE FLUCTUATES WHILE ENGINE IS AT 100 PERCENT. NEEDLE FLUCTUATES FROM 70 PERCENT - 25 PERCENT INTERMITTENTLY. LAST REPAIR WAS ALSO FLUCTUATES, STILL DOING THE SAME THING.