N160PB

Part: FITTING — CORRODED (ZONE 600) · airframe 29,775 hrs · 20,341 cycles

DURING MAINTENANCE A SPOT OF CORROSION WAS VISUALLY IDENTIFIED ON THE AFT FACE OF THE FWD RH UPPER FUSELAGE ATTACH FITTING PN: 0811350-9. THIS CORROSION MEASURES .275 WIDE, AND .226 TALL, WITH AN APPROXIMATE DEPTH OF .018 AND IS CONSISTENT WITH OTHER CORROSION VISUALLY IDENTIFIED IN THE PAST. THIS FITTING HAS BEEN CHANGED USING NEW PARTS.

Part: FITTING — CRACKED (LT NACELLE) · airframe 27,271 hrs · 16,919 cycles

DURING NDT INSPECTION AS NOTED IN SID 57-10-16, A CRACK WAS DISCOVERED ON THE LEFT HAND OUTBOARD NACELLE FITTING (P/N: 5292029-23). THIS CRACK MEASURES APPROXIMATELY .210 INCHES LONG ON THE OUTBOARD LOWER LEG OF THE FITTING AND IS CONSISTENT WITH OTHER CRACKS FOUND USING THE LIGHTED BORESCOPE INSPECTION TECHNIQUE (TEXTRON MEL54-02R2) TO SATISFY REQUIREMENT OF AD2017-10-09. THIS FITTING WILL BE REPLACED USING NEW PARTS.

Part: FITTING — CRACKED (NACELLE) · airframe 26,959 hrs · 38,538 cycles

DURING A ROUTINE INSPECTION, A CRACK WAS IDENTIFIED ON THE OUTBOARD LEG OF THE RIGHT HAND INBOARD FITTING. THIS CRACK MEASURES APPROXIMATELY .598 AND WAS DISCOVERED USING THE LIGHTED BORESCOPE INSPECTION CRACK IS CONSISTENT WITH OTHER THAT HAVE BEEN IDENTIFIED USING THE SAME INSPECTION PROCEDURE. THIS FITTING WILL BE REPLACED WITH A FACTORY NEW PART.

Part: FITTING — CRACKED (NACELLE) · airframe 26,959 hrs · 38,538 cycles

DURING A ROUTINE INSPECTION, TWO CRACKS WERE IDENTIFIED ON THE RIGHT HAND OUTBOARD FITTING (P/N 5292029-24.) THE FIRST CRACK WAS ON THE OUTBOARD LEG AND MEASURES APPROXIMATELY .130. THE SECOND CRACK WAS ON THE INBOARD LEG AND MEASURES APPROXIMATELY .105. BOTH CRACKS WERE DISCOVERED USING THE LIGHTED BORESCOPE INSPECTION PROCEDURE AS OUTLINED IN MEL-54-02R2 TO SATISFY AD2017-10-19. THESE CRACKS ARE CONSISTENT WITH OTHERS THAT HAVE BEEN IDENTIFIED USING THE SAME INSPECTION PROCEDURE. THIS FITTING WILL BE REPLACED WITH A FACTORY NEW PART.

Part: VALVE — LEAKING (BRAKE) · airframe 25,769 hrs

PILOT REPORTED NO BRAKING PRESSURE WHEN LEAVING THE GATE. MAINTENANCE INSPECTED AND FOUND THE PARKING BRAKE VALVE LEAKING, THE PART WAS REPLACED WITH NO FURTHER DEFECTS.

Part: VALVE GUIDE — DAMAGED (NR 3 CYLINDER) · airframe 24,015 hrs · 12,709 cycles

PILOT REPORTED RIGHT ENGINE SURGE 1 INCH MANIFOLD PRESSURE DURING TAKE OFF POWER USE. MAINTENANCE INSPECTED AND REPLACED THE NR 3 CYLINDER ASSEMBLY, AS WELL AS THE NR 1 & NR 3 CYLINDER EXHAUST AND INTAKE HYDRAULIC LIFTERS. FURTHER DISASSEMBLY OF THE CYLINDER ASSEMBLY FOUND VALVE GUIDE DAMAGE.

Part: FITTING — CRACKED (LT NACELLE) · airframe 23,966 hrs · 12,623 cycles

DURING A ROUTINE INSPECTION, A CRACK WAS DISCOVERED IN THE LT INBOARD NACELLE FITTING. THE CRACK WAS DISCOVERED ON THE OUTBOARD SIDE, JUST FORWARD OF THE SPAR STRAP. CRACK LENGTH IS .117.

Part: EXHAUST VALVE — DAMAGED (NR 2 CYLINDER) · airframe 23,846 hrs

PILOT REPORTED RIGHT ENGINE RUNS ROUGH AND HAS SLIGHT VIBRATION AT CERTAIN PHASES OF FLIGHT. CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 3 CYLINDER) · airframe 23,846 hrs

PILOT REPORTED RIGHT ENGINE RUNS ROUGH AND HAS SLIGHT VIBRATION AT CERTAIN PHASES OF FLIGHT. CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 5 CYLINDER) · airframe 23,846 hrs

PILOT REPORTED RIGHT ENGINE RUNS ROUGH AND HAS SLIGHT VIBRATION AT CERTAIN PHASES OF FLIGHT. CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 3 CYLINDER) · airframe 23,769 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 4 CYLINDER) · airframe 23,497 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 3 CYLINDER) · airframe 23,497 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — CRACKED (NR 1 CYLINDER) · airframe 23,497 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE CRACKED AND DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — DAMAGED (NR 5 CYLINDER) · airframe 23,497 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: EXHAUST VALVE — CRACKED (CYLINDER) · airframe 23,497 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE CRACKED AND DISPLAYS EVIDENCE OF HEAT DAMAGE.

Part: BLOWER — MALFUNCTIONED (HEATER) · airframe 21,963 hrs · 9,564 cycles

PILOT REPORTED HEATER INOPERATIVE, SMOKE SMELL EN-ROUTE. R & R HEATER BLOWER & FUEL PUMP. ALL OPERATIONAL CHECKS GOOD.

Part: DRAG BRACE — CRACKED (NLG) · airframe 20,475 hrs

AT SCHEDULED INSPECTION, NLG DRAG BRACE, OEM PN 5142002-5, WAS FOUND TO BE CRACKED IN THE AREA OF NLG ACTUATOR ATTACH POINT. METHOD OF INSPECTION WAS DYE PENETRANT. THIS CRACK WAS FOUND TO BE BEYOND LIMIT ALLOWABLE. THIS UNIT HAS BEEN SCRAPPED & A REPLACEMENT DRAG BRACE HAS BEEN INSTALLED IN ACFT.

Part: DRAG BRACE — CRACKED (NLG)

AT SCHEDULED INSPECTION, NLG DRAG BRACE, OEM PN 5142002-5, WAS FOUND TO BE CRACKED IN THE AREA OF NLG ACTUATOR ATTACH POINT. METHOD OF INSPECTION WAS DYE PENETRANT. THIS CRACK WAS FOUND TO BE WITHIN ALLOWABLE LIMIT. THIS UNIT HAS BEEN REPAIRED IAW PROCEDURE OUTLINED IN MEB941-11R1 & RETURNED TO SERVICE.

Part: HSI — FAILED (COCKPIT) · airframe 16,172 hrs

CREW REPORTED, IN CRUISE CONFIGURATION, SMOKE WAS NOTICED BEHIND THE GLASS OF THE HORIZONTAL SITUATION INDICATOR. SMOKE WAS CONTAINED INSIDE THE INDICATOR, BUT THE CABIN DID HAVE AN ACRID BURNING ODOR. UNIT CIRCUIT BREAKER WAS PULLED WHICH STOPPED THE SMOKE. CONTINUED TO FINAL DESTINATION WITH NO FURTHER ISSUES. MX R & R KI-525A HSI. ACFT RELEASED BACK TO SERVICE.

Part: FITTING — CORRODED (VERTICAL STAB)

VERTICAL STABILIZER FORWARD SPAR ATTACH FITTING AT FUSELAGE, FOUND CORRODED. (X)