N261PA

Part: NONE — NONE (ZONE 600) · airframe 11,542 hrs · 7,898 cycles

AIRCRAFT IMPACTED A DEER ON LANDING AT KPYM. RIGHT TRAILING EDGE FLAP WAS DAMAGED BEYOND REPAIR AND WAS REPLACED.

Part: NONE — NONE · airframe 11,486 hrs · 7,852 cycles

AIRCRAFT WAS ON SHORT FINAL TO KPYM, PLYMOUTH, MA MUNICIPAL AIRPORT, FULLY CONFIGURED FOR LANDING, WHEN PILOTS SAW SMOKE AND HEARD A POPPING SOUND FROM THE COPILOTS INSTRUMENT PANEL NEXT TO THE GEAR HANDLE. A FLAME WAS BRIEFLY OBSERVED BY THE COPILOT IN THE SAME AREA. THE CAUSE OF THIS ISSUE IS CURRENTLY BEING INVESTIGATED BY CRS ZKFR180L AT KPYM. THIS SDR WILL BE REVISED AS TO CAUSE. NOTE-PROPELLER LISTED ABOVE IS #2 ENGINE

Part: HINGE — CORRODED (AILERON TRIM TAB) · airframe 11,353 hrs · 7,767 cycles

RH AILERON SIGNIFICANT CORROSION FOUND AT CENTER TRIM TAB HINGE, AROUND BONDING STRAP ATTACHMENT HOLE, IN AFT SPAR STRUCTURE. TEXTRON ENGINEERING NOTIFIED AND NO REPAIR ALLOWED. NO NEW REPLACEMENT AILERONS AVAILABLE. ACQUIRED AS REMOVED RH AILERON S/N DHB1002 AND SAME IRREPARABLE CORROSION FOUND. ACQUIRED SECOND AS REMOVED RH AILERON S/N DHB1032 AND SAME IRREPARABLE CORROSION FOUND. WE NOW HAVE THREE RH AILERONS FROM THREE DIFFERENT AIRCRAFT WITH UNAIRWORTHY RH AILERONS DUE TO SIGNIFICANT CORROSION OF THE AFT SPAR STRUCTURAL CASTINGS.

Part: ATTACH FITTING — CORRODED (ZONE 300) · airframe 9,084 hrs · 5,483 cycles

DURING SCHEDULED INSPECTION, FOUND CORROSION ON LT SIDE OF VERTICAL TO HORIZONTAL STABILIZER ATTACH FITTING. CORROSION IS INTERGRANULAR, AND IS LOCATED AROUND 12 FASTENER HEADS.

Part: O-RING — LEAKING (WHEEL HALVE) · airframe 8,884 hrs · 5,835 cycles

DURING PREFLIGHT, FLIGHT CREW NOTICED LT OTBD TIRE LOOKED LOW. MX DISCOVERED TIRE ALMOST COMPLETELY DEFLATED BUT NOT BLOWN. WHEEL ASSYS ONLY HAD 9 CYCLES SINCE IT WAS O/H. REMOVED AND REPLACED WHEEL/TIRE ASSY. INSPECTED REMOVED WHEEL ASSY AND FOUND AIR LEAKING FROM RIM NEAR VALVE STEM LOCATION (BUT NOT FROM VALVE STEM). MX BELIEVES THAT LEAK IS COMING FROM THE WHEEL HALF SEALING O-RING.

Part: O-RING — LEAKING (WHEEL HALVES) · airframe 8,894 hrs · 5,844 cycles

DURING PREFLIGHT, FLIGHT CREW NOTICED LT INBD TIRE LOOKED LOW. MX DISCOVERED TIRE ALMOST COMPLETELY DEFLATED BUT NOT BLOWN. WHEEL ASSYS ONLY HAD 9 CYCLES SINCE IT WAS O/H. R & R WHEEL/TIRE ASSY. INSPECTED REMOVED WHEEL ASSY AND FOUND AIR LEAKING FROM RIM NEAR VALVE STEM LOCATION (BUT NOT FROM VALVE STEM). MX BELIEVES THAT LEAK IS COMING FROM THE WHEEL HALF SEALING O-RING. THEY ALSO NOTICED THE WHEEL HALF SEALING O-RING WAS A DIFFERNT COLOR (BLUE) THAN NORMAL (BLACK).

Part: CHECK VALVE — LEAKING (OXYGEN SYSTEM) · airframe 8,748 hrs · 5,704 cycles

OXYGEN SYS NON-RETURN VALVE LEAKING ALLOWING OXYGEN TO FLOW BACKWARDS AND LEAK OUT OF FILLER PORT. THIS WAS A BRAND NEW CHECK VALVE FROM MFG. REMOVED AND REPLACED UNIT.

Part: CHECK VALVE — LEAKING (OXYGEN SYSTEM) · airframe 8,748 hrs · 5,704 cycles

OXYGEN SYSTEM LEAKING: FOUND OXYGEN SYSTEM NON-RETURN VALVE INOP AND ALLOWING OXYGEN TO FLOW BACKWARDS AND LEAKING OUT OF FILLER PORT. REMOVED AND REPLACED NON-RETUEN VALVE AND LEAK CHECKED GOOD. THIS NON RETURN VALVE WAS JUST INSTALLED 9 MONTHS AGO FOR THE SAME ISSUE.

Part: SKIN — DELAMINATED (ZONE 400) · airframe 8,693 hrs · 5,661 cycles

DURING ENGINE CHANGE, CORE COWL SEGMENT FOUND DELAMINATED. MFG HAS A REPAIR FOR THIS PROBLEM BUT UNFORTUNATELY THE EXTENT OF DAMAGE TO THIS CORE COWL IS BEYOND ALL LIMITS OF REPAIR. THE REPAIR IS USUALLY FOR A SMALL AMOUNT OF LIFTING AT THE CORNERS OF THE BONDMENT. MFG INFORMED THAT IT DOES NOT HOLD PMA FOR THIS PROGRAM SO THE NEW PART WILL NEED TO BE PURCHASED THROUGH HBP&D. RDO INFORMED THAT THEY ARE NOT ABLE TO PRODUCE A REPAIR FOR THIS ISSUE. THIS IS DUE TO THE ACOUSTIC PROPERTIES OF THE COWL. THE COWL MUST BE REPLACED WITH NEW OR SERVICEABLE PART. R & R CORE COWL SEGMENT.

Part: CONTROLLER — FAULTY (CABIN TEMP) · airframe 8,595 hrs · 5,605 cycles

CABIN TEMPERTURE UNCONTROLLABLE IN AUTO MODE. FOUND CABIN TEMPERTURE CONTROLLER NOT PROVIDING ANY OUTPUT VOLTAGE. CONTROLLLER GIVES MOMENTARY PULSES ONLY VISIBLE USING A TEST LAMP WHICH CAUSES TEMP CONTROL VALVE TO "CLICK" BUT NOT ENOUGH TO MOVE VALVE. R & R CABIN TEMP CONTROLLER. OPS CHECKED GOOD.

Part: STARTER GEN — FAILED (NR 2 ENGINE) · airframe 8,400 hrs · 5,440 cycles

ACFT EXPERIENCED MODERATE VIBRATION IN CRUISE, FLIGHT CREW FELT VIBRATION WAS FROM NR 2 ENGINE, FOLLOWED SHORTLY AFTER WITH GEN 2 FAIL INDICATION, CREW SHUTDOWN NR 2 ENGINE, FLIGHT DIVERTED FOR NON-EVENTFUL SINGLE ENGINE LANDING. MX REMOVED NR 2 ENGINE STARTER GEN UNIT, FOUND UNIT FAILED, WITH INTERNAL COOLING FAN ASSY CONTACTING GENERATOR SHROUD. STARTER GEN UNIT HAD 305.1 HOURS SINCE O/H, THIS UNIT TBO IS 1000 HOURS.

Part: STARTER GEN — DESTROYED (ZONE 400) · airframe 8,314 hrs · 5,393 cycles

DURING CRUISE FLIGHT, EXPERIENCED VIBRATION, BELIEVED TO BE FROM ENGINE AREA. VIBRATION INCREASED, BUT DID NOT SHOW ON EVM INDICATOR, FOLLOWED BY GEN 1 FAIL INDICATION, WITH BUS TIE CLOSED IN FLIGHT. ACFT MADE UNSCHEDULED LANDING. MX FOUND NR1 STARTER GEN FAILED, COOLING FAN ON GEN SHATTERED, SHAFT SHEARED, MANY BROKEN PIECES OF UNIT IN ENGINE COWLING.

Part: POSITION SWITCH — DAMAGED (TE FLAPS)

DURING TAKEOFF, ENROUTE, THE LANDING GEAR HORN SOUNDED WHEN GEAR LEVER WAS PLACED IN UP POSITION, BOTH WITH FLAPS IN 15 DEGREE AND 0 DEGREE POSITION. CREW PLACED GEAR LEVER IN DOWN POSITION AND HORN SILENCED. CREW CIRCLED AND BURNED OFF FUEL AND RETURNED TO DEPARTURE AIRPORT AND LANDED SAFELY. DID NOT DECLARE EMERGENCY. AC WAS FERRIED TO HOME BASE FOR MAINTENANCE. UPON INVESTIGATION IT WAS FOUND THAT THE FLAP POSITION SWITCH WAS AT FAULT. REMOVED AND REPLACED RT THROTTLE QUADRANT FLAP SWITCH WITH NEW. PERFORMED OPS CHECK OF GEAR HORN SYSTEM. OPS CHECK, NORMAL AND AC RETURNED TO SERVICE.