N613NA

Part: CONTROL VALVE — INTERMITTENT (ECS) · airframe 11,446 hrs · 19,795 cycles

FLIGHT NURSE NOTIFIED PILOT OF A BURNING SMELL IN BACK OF CABIN. NO FIRE WARNING INDICATIONS OR ENG INSTRUMENT IRREGULARITIES WERE SHOWING & NO SIGNS OF BURNING SMELL OR FIRE IN COCKPIT UNTIL SEVERAL MINUTES LATER. PILOT WAS BESIEGED WITH A NOXIOUS, CHEMICAL BURNING SMELL, THE AFT CABIN WAS FILLED WITH A HAZY, WHITE SMOKE LEADING TO DESTINATION DIVERSION. DURING TROUBLESHOOTING NOTED THAT THE ECS CONTROL VLV WAS INTERMITTENT IN HOT COLD & REPLACED. ECS WAS WORKING CORRECTLY WITH NO FURTHER FAULTS.

Part: STRAKE — CRACKED (RUDDER) · airframe 9,656 hrs · 16,359 cycles

STRAKE ATTATCHED TO THE T/E OF THE RUDDER TRIM TAB CRACKED ALONG RIVET LINE VERTICALLY TO APPROX 3 IN FROM THE BOTTOM, WHERE THE CRACK EXTENDED OUTWARDS TO THE LT EDGE. THE STRAKE IS APPROX 3 IN WIDE AND IS ATTACHED TO THE TABS T/E WITH A RIVET LINE AT THE CTR AND EXTENDS AN INCH ON EITHER SIDE OF THE TAB, WITH NO SUPPORT.

Part: WINDSCREEN — CRACKED (RIGHT) · airframe 9,312 hrs

RT FWD WINDSHIELD CRACKED DURING FLIGHT. ACFT RETURNED TO AIRPORT WITHOUT INCIDENT.

Part: INLET — BURNED (ENGINE) · airframe 8,943 hrs

UPON DEPARTING, PILOT NOTICED A BURNING SMELL FOLLOWING GEAR RETRACTION. PILOT CONFIRMED THE ODOR IN THE CABIN WITH THE CLINICAL CREW MEMBERS AND THEN ELECTED TO RETURN FOR A PRECAUTIONARY LANDING. MECHANIC RESPONSE TO DUPLICATE THE ODORS, HAD PILOT RUN THE ENGINE, AND AT TAKEOFF POWER, A BURNING SMELL WAS NOTED COMING FROM THE ECS DUCTING. VISUALLY INSPECTED THE ECS DUCTING, AND TOOK TEMP MEASUREMENTS OF ECS OUTLET AIR IN MANUAL AND AUTO MODE TO VERIFY THAT THE DUCT TEMP SENSOR AND DUCT OVER TEMP SENSOR WERE FUNCTIONING PROPERLY. NO DEFECTS COULD BE FOUND WITH THE ECS DUCTING. INSPECTED ENG INLET AND ENG COMPRESSOR AND FOUND FWD ENG COWL TO HAVE BURNED AND DETERIORATED COMPOSITE MATERIAL ON ENGINE INLET DEICE LIP. INSTALLED A SERVICEABLE LOANER COWL, RAN ENGINE AT TAKEOFF POWER, AND NO ODORS WERE NOTED FROM THE ECS DUCTING. ACCOMPANIED THE PILOT ON AN OPS CHECK FLIGHT, AND NO ODORS WERE NOTED FROM THE ECS DUCTING.

Part: SWITCH — FAILED (DUCT TEMP) · airframe 3,937 hrs · 5,835 cycles

TEMP CONTROL SYSTEM SENT SIGNAL TO TEMP CONTROL VALVE TO GO FULL HOT. DUCT TEMP SWITCH FAILED TO ILLUMINATE ECS LIGHT AND SHUT DOWN SYSTEM. CHANGED DUCT TEMP SWITCH AND TEMP CONTROLLER, SYSTEM OPS GOOD.

Part: CHECK VALVE — FAILED (FUEL SYSTEM) · airframe 3,779 hrs · 5,397 cycles

FUEL TRANSFERS FROM RT TO LT WING WHILE AIRCRAFT IS NOT IN USE.

Part: DRIVE SHAFT — SHEARED (NR 2 GEN) · airframe 3,765 hrs · 5,367 cycles

NR 2 GENERATOR DROPPED OFF LINE. AFTER TROUBLESHOOTING PROBLEM, FOUND NR 2 GENERATOR DRIVE SHAFT SHEARED.

Part: SEAL — LEAKING (REDUCTION GB) · airframe 3,750 hrs · 5,354 cycles

OIL LEAKING FROM REDUCTION GEARBOX AREA.

Part: INDICATOR — WORN (ATTITUDE) · airframe 3,709 hrs · 5,512 cycles

STANDBY ATTITUDE INDICATOR WILL NOT CAGE.

Part: SENSOR — FAILED (OAT) · airframe 3,688 hrs · 5,461 cycles

PROP HEAT CAWS ILLUMINATED IN FLIGHT.

Part: TRANSDUCER — FAILED (TORQUE INDICATOR) · airframe 3,662 hrs · 5,403 cycles

TORQUE INDICATION SHOWS ZERO TORQUE AT IDLE.

Part: PDU — FAILED (TE FLAPS) · airframe 3,625 hrs · 5,372 cycles

FLAPS STUCK AT 0 DEGREES.

Part: ACTUATOR — LEAKING (RT MLG) · airframe 2,864 hrs · 4,186 cycles

DURING 100 HR INSPECTION, FOUND RIGHT GEAR ACTUATOR SEEPING HYDRAULIC FLUID DURING RETRACTION TESTS. REMOVED AND REPLACED ACTUATOR WITH SERVICEABLE PART IAW AMM CHPT 32 AND OPS CHECK OK.