N72649

Part: INDICATOR — MALFUNCTIONED (MLG) · airframe 20,341 hrs

AFTER TAKEOFF, PLACED LANDING GEAR CONTROL LEVER UP, THE 3 GREEN LIGHTS EXTINGUISHED, BUT THE RED UNSAFE LIGHT REMAINED ON. WHILE THE ACFT WAS BEING SLOWED, IAW THE EMERGENCY PROCEDURES CHECKLIST.

Part: SEAT BACK — CRACKED (COCKPIT) · airframe 18,640 hrs

SEAT BACK FRAME CRACKED.

Part: BEARING — ROUGH (GYRO) · airframe 18,640 hrs

GYRO REMOVED FOR ROUGH BEARINGS AND LOUD NOISE.

Part: STARTER GEN — MALFUNCTIONED (NR 2) · airframe 17,506 hrs

NR 2 STARTER GENERATOR LIGHT COME ON IN FLIGHT. FOLLOWED EMERGENCY CHECK LIST. WHEN COMPLETING THE CHECKLIST THE NR 2 OIL PRESSURE GAGE WENT TO ZERO. NOTED THAT NO WARNING LIGHT WAS ON FOR THE NR 2 OIL PRESSURE SYSTEM. MAINTAINED A WATCH ON THE TEMPERATURE AND RETURNED TO DEPARTURE.

Part: HOSE — FAILED (HYD SYSTEM) · airframe 17,284 hrs · 34,684 cycles

NR 2 SERVO SYSTEM CAUTION LIGHT ILLUMINATED APPX. 15 MINUTES INTO THE FIRST FLIGHT OF THE DAY, ACCOMPANIED BY NR 2 HYDRAULIC PRESSURE FLUCTUATING 2000 AND 3000 PSI. EMERGENCY PROCEDURE WAS COMPLETED PER THE EP CHECKLIST. ENROUTE TO LEEVILLE WITH SYSTEM NR 2 SECURED, NR 2 HYDRAULIC PRESSURE FLUCTUATED BETWEEN 0-3000 PSI. NORMAL LANDING GEAR EXTENSION WAS NOT ATTEMPTED DUE TO INADEQUATE PRESSURE. LANDING GEAR WAS EXTENDED USING EMERGENCY BLOW-DOWN SYSTEM. AIRCRAFT WAS LANDED WITHOUT FURTHER INCIDENT.

Part: ROD END — CRACKED (MLG)

WHILE PERFORMING THE REQUIREMENTS OF ASB 76-32-26, CORROSION INSPECTION OF THE THREADED JOINT, FOUND BEARING CRACKED. REPLACED POSITIONING ROD END. (X)

Part: HOSE — BINDING (M/R DAMPER)

WHILE INSPECTING M/R DAMPERS, THE BLACK DAMPER HOSE WAS FOUND BINDING WHEN THE DAMPER WAS ROTATED. THE INBOARD FERREL WAS ALSO FOUND TURNING WHEN HOSE WAS ROTATED. REPLACED HOSE, THE BAD NOSE WAS FOUND TO BE .50 INCH SOFTER THAN THE NEW HOSE. (X)

Part: BRUSHES — WORN (STARTER GEN)

PART IS PITTED, BRUSHES REPLACED. (X)

Part: POTENTIOMETER — FAILED (AFSC ACTUATOR)

FEEDBACK POTENTIOMETER PREMATURE FAILURE, CAUSES ACTUATOR TO KICK IN-FLIGHT. (X)

Part: POTENTIOMETER — FAILED (AFCS)

SUBMITTER STATED POTS WEAR OUT LONG BEFORE THE OVERHAUL OF 3,000.00 HOURS. FEEDBACK POT PREMATURE FAILURE, SHOULD LAST UNTIL OVERHAUL TIME OF 3,000 HOURS. CAUSED ACTUATOR TO KICK IN-FLIGHT. COMPONENT P/N 7690001802106.

Part: BLADE — DELAMINATED (MAIN ROTOR)

SKIN DELAMINATED ON TOP FROM STA 32 EXTENDING OUT TO STA 105, 6 INCHES BACK FROM LEADING EDGE ABOUT 5 INCHES. (X)

Part: COUPLING — CRACKED (INTERMED GRBOX)

COUPLING WAS FOUND CRACKED IN 7 PLACES. IT WAS LOCATED AT THE INTERMEDIATE GEARBOX OUTPUT FLANGE. THE PREVIOUS COUPLING WAS ALSO CRACKED. THE RUN-OUT WAS CHECKED AND FOUND WITHIN MANUFACTURER'S LIMITS. THE NR 5 T/R DRIVESHAFT AND INTERMEDIATE GEARBOX WERE REMOVED FOR FURTHER EVALUATION. NEW COUPLING WAS INSTALLED. RUN-OUT CHECK IS WITHIN MANUFACTURER'S LIMITS.

Part: LENS — SPLIT (STROBE)

BRAND NEW PART OUT OF STOCK, SPLIT ALONG GLUE LINE. LENS HALVES NOT BONDED TOGETHER PROPERLY. THIS WAS TO REPLACE THE LENS INSTALLED THAT WAS REMOVED FOR THE SAME REASON.

Part: LENS — SPLIT (STROBE)

STROBE LIGHT LENS SPLIT IN HALF, GLUE DOES NOT HOLD HALVES TOGETHER ALONG BOND LINE.

Part: BLADE — DISBOND (MAIN ROTOR)

TWO AREAS OF DISBOND ON MAIN ROTOR BLADE. (TOP SURFACE STARTS AT BLADE STA 232 AND EXTENDS SPANWISE APPROXIMATELY 4 INCHES ALONG LEADING EDGE STRIP, EXTENDING AFT APPROXIMATELY 4 INCHES CHORDWISE). LOWER SURFACE STARTING AT BLADE STA 237, APPROXIMATELY EXTENDING SPANWISE 4 INCHES, LOCATED AFT OF LEADING EDGE 3 INCHES APPROX .75 IN CHORDWISE.