N375R

Part: TORQUE TUBE — BROKEN (RUDDER PEDALS) · airframe 31,056 hrs · 39,222 cycles

WHEN ACTUATING THE RUDDER PEDAL WHILE MANEUVERING INTO A PARKING SPACE, THE PILOT REPORTED THAT THE RIGHT RUDDER PEDAL HAD BROKEN OFF THE TORQUE TUBE. MAINTENANCE INSPECTED AND FOUND IT BROKEN OFF AT THE WELD. THIS WAS REPLACED BY MAINTENANCE WITH NO FURTHER DEFECTS NOTED.

Part: FITTING — CRACKED (RT NACELLE) · airframe 30,681 hrs · 38,785 cycles

WHILE PERFORMING INITIAL NDT INSPECTION (HFEC) TO SATISFY THE REQUIREMENTS OF TEXTRON SID 57-10-16, A CRACK WAS FOUND ON THE RIGHT HAND INBOARD NACELLE FITTING. THIS CRACK WAS FOUND ON THE OUTBOARD SIDE OF THE FITTING, AND MEASURES .175 IN LENGTH. THIS CRACK IS CONSISTENT WITH OTHER'S THAT HAVE BEEN IDENTIFIED USING THE SAME PROCEDURE. THIS FITTING WILL BE REPLACED USING FACTORY NEW PARTS.

Part: FITTING — CRACKED (RT NACELLE) · airframe 30,263 hrs · 38,252 cycles

WHILE PERFORMING LIGHTED BORESCOPE INSPECTION PROCEDURE AS OUTLINED IN TEXTRON MEL-54-02R2 TO SATISFY AD2017-10-09, A CRACK WAS IDENTIFIED IN THE OUTBOARD RADIUS OF THE RIGHT HAND OUTBOARD NACELLE FITTING. THIS CRACK MEASURES .300 INCHES LONG AND IS CONSISTENT WITH OTHERS FOUND USING THIS TECHNIQUE. THIS FITTING HAS BEEN REMOVED AND REPLACED WITH SUPERSEDED PART NUMBER 5292029-32.

Part: EXHAUST VALVE — DAMAGED (NR 5 CYLINDER) · airframe 26,535 hrs

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

Part: EXHAUST VALVE — DAMAGED (NR 4 CYLINDER) · airframe 26,231 hrs

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

Part: PISTON RING — LEAKING (NR 5 CYLINDER) · airframe 26,171 hrs

CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. SHOWS EVIDENCE OF PISTON RING BLOW-BY.

Part: GASKET — TORN (HEATER) · airframe 25,370 hrs · 31,929 cycles

PILOT REPORTED FUEL SMELL IN COCKPIT. INSPECTED & FOUND HEATER FUEL FILTER GASKET IN RT WING TORN & LEAKING. R & R HEATER FUEL FILTER GASKET WITH NEW IAW 402-C IPC CH 21-40-00 FIG 2. LEAK & OPERATIONS CHECKED GOOD.

Part: WARNING SWITCH — OUT OF ADJUST (DOOR) · airframe 24,163 hrs · 30,215 cycles

THE DOOR WARNING LIGHT ILLUMINATED IN FLIGHT. ALL DOORS REMAINED SECURE IN FLIGHT. ADJUSTED THE EMER EXIT WARNING SWITCH IAW MM 52-70-00 WITH NO FURTHER DEFECT NOTED.

Part: SPAR CAP — CORRODED (RT WING) · airframe 23,517 hrs

DURING SCHEDULED INSPECTION, AREAS OF EXFOLIATING CORROSION WAS FOUND AT RT WING LWR FWD SPAR CAP STRAP OEM PN 5292029-2 PREVIOUSLY INSTALLED TO SATISFY REQUIREMENT OF AD2005-12-13 CONCURRENT WITH MEB05-2 AS TERMINATING ACTION FOR AD2005-05-52. THE DAMAGE HAS BEEN BLENDED & MEASUREMENTS HAVE BEEN SUBMITTED & SUBSEQUENTLY REVIEWED BY ENGINEERING DEPARTMENT. ENGINEERING ADVISES REPLACEMENT OF AFFECTED PARTS DUE TO DEPTH OF BLENDS REQUIRED TO REMOVE VISIBLE CORROSION. THE AFFECTED PARTS WILL BE REPLACED. PRIOR TO REMOVAL OF STRAP 5292029-2, AN EDDY CURRENT INSPECTION OF ENTIRE STRAP WAS PERFORMED IAW SID57-10-16. MULTIPLE AREAS OF SUBSURFACE CORROSION WERE FOUND TO BE PRESENT WITHIN STRAP. THESE ANOMALIES WERE NOT DETECTED AT DETAILED VISUAL INSPECTION FOLLOWING BLEND EFFORT. A SUPPLEMENT ILLUSTRATING DAMAGE LOCATIONS & SEVERITY OF CORROSION HAS BEEN SUBMITTED WITH THIS REPORT.

Part: SPAR CAP — CORRODED (LT WING) · airframe 23,517 hrs

DURING SCHEDULED INSPECTION, AREAS OF EXFOLIATING CORROSION WAS FOUND AT LT WING LWR FWD SPAR CAP STRAP OEM PN 5292029-1 PREVIOUSLY INSTALLED TO SATISFY REQUIREMENT OF AD2005-12-13 CONCURRENT WITH MEB05-2 AS TERMINATING ACTION FOR AD2005-05-52. THE DAMAGE HAS BEEN BLENDED & MEASUREMENTS HAVE BEEN SUBMITTED & SUBSEQUENTLY REVIEWED BY ENGINEERING DEPARTMENT. ENGINEERING ADVISES REPLACEMENT OF AFFECTED PARTS DUE TO DEPTH OF BLENDS REQUIRED TO REMOVE VISIBLE CORROSION. THE AFFECTED PARTS WILL BE REPLACED. PRIOR TO REMOVAL OF STRAP 5292029-1, AN EDDY CURRENT INSPECTION OF ENTIRE STRAP WAS PERFORMED IAW SID57-10-16. MULTIPLE AREAS OF SUBSURFACE CORROSION WERE FOUND TO BE PRESENT WITHIN STRAP, THESE ANOMALIES WERE NOT DETECTED AT DETAILED VISUAL INSPECTION FOLLOWING BLEND EFFORT. A SUPPLEMENT ILLUSTRATING DAMAGE LOCATIONS & SEVERITY OF CORROSION HAS BEEN SUBMITTED WITH THIS REPORT.

Part: SPAR — CRACKED (ZONE 100) · airframe 22,370 hrs

DURING A SCHEDULED MX EVENT, CRACKS WERE NOTED IN THE FORWARD AND AFT SPAR WEBS ON THE REAR SPAR. DAMAGE WAS LOCATED AT FLOOR SUPPORT ATTACH POINTS. ENGINEERING WAS REQUESTED AND RECEIVED AND REPAIRS ARE CURRENTLY UNDERWAY.

Part: DRAG BRACE — CRACKED (NLG) · airframe 21,960 hrs

AT SCHEDULED INSPECTION, NLG DRAG BRACE, 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 OF MEB91-11R1. THIS UNIT HAS BEEN SCRAPPED & A REPLACEMENT DRAG BRACE HAS BEEN INSTALLED IN ACFT.

Part: PROPELLER — MALFUNCTIONED (RIGHT) · airframe 21,808 hrs

PILOT REPORTED THAT THE RT PROPELLER WENT TO FEATHER UNCOMMANDED ON TAKEOFF ROLL. UPON ARRIVAL BY MX, THE ENGINE WAS INSPECTED WITH NO DEFECTS NOTED. AS A PRECAUTION, R & R RIGHT PROP GOVERNOR. GROUND RAN LT AND RT ENGINES WITH ALL PARAMETERS OPERATIONALLY CHECKED OK.

Part: WIRE — BROKEN (DOWNLOCK SWITCH) · airframe 20,964 hrs

CREW REPORTED, ON APPROACH TO LAND, LANDING GEAR WAS EXTENDED BUT LT MAIN GEAR DOWN AND LOCK LIGHT FAILED TO ILLUMINATE. LAMP PRESS TO TEST OK. GEAR WARNING HORN DID NOT SOUND FOR THROTTLE OR FLAP TEST. ALTERNATE GEAR EXTENSION WAS PERFORMED PER "GEAR WILL NOT EXTEND HYDRAULICALY CHECK LIST" (BLOWDOWN)BUT DOWN AND LOCK LIGHT STILL FAILED TO ILLUMINATE. EMERGENCY WAS DECLARED, APPROACH WAS CONTINUED, LANDING WAS UNEVENTFUL. MAINTENANCE INSPECTED AIRCRAFT, FOUND BROKEN WIRE ON DOWN/LOCK SWITCH.REMOVED AND REPLACED ACTUATOR ASSEMBLY AS A PRECAUTIONARY MEASURE.EXTENSION AND RETRACTION TEST PERFORMED, CHECKS OK. AIRCRAFT RELEASED BACK TO SERVICE.

Part: DRAG BRACE — CRACKED (NLG) · airframe 20,905 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 WITHIN ALLOWABLE LIMIT. THIS UNIT HAS BEEN REPAIRED IAW PROCEDURE OUTLINED IN MEB941-11R1 & RETURNED TO SERVICE.

Part: ACTUATOR — WORN (ELEVATOR TRIM) · airframe 19,641 hrs

CREW REPORTED ELEVATOR TRIM RANGE OF MOTION INSUFFICIENT FOR FLIGHT. ELEVATOR TRIM STOPPED AT LEAST ONE FULL ROTATION BEFORE COCKPIT FORWARD LIMIT. ALSO COCKPIT TRIM TAB INDICATOR READS INCORRECTLY. MAINTENANCE REMOVED AND REPLACED ELEVATOR TRIM TAB ACTUATOR, CHECKED ELEVATOR TRIM RIGGING, REINDEXED ELEVATOR TRIM WHEEL INDICATOR.

Part: SWITCH — CONTAMINATED (NLG) · airframe 18,578 hrs

ON LANDING AT ACK, NOSE LANDING GEAR FAILED. PILOT HAD 3 GREEN DOWN AND LOCKED INDICATIONS PRIOR TO AND AFTER LANDING. AFTER SECURING GEAR DOWN AND LOCKED, REMOVING AND REPLACING BOTH PROPELLERS, AN ENGINE RUN UP, AND INSPECTION, AIRCRAFT FERRY FLOWN TO MAINTENANCE BASE FOR FURTHER INVESTIGATION. PART WAS INSPECTED AND OVERHAULED. UPON INITIAL INSPECTION NO DAMAGE WAS NOTED. UPON TEARDOWN EVIDENCE OF WATER WAS FOUND IN COVER. SUSPECT FREEZE UP OF TOWER AND SWITCH MECHANISM. UNIT HAS BEEN RETURNED TO SERVICE.

Part: MASTER SWITCH — INOPERATIVE (COCKPIT) · airframe 18,500 hrs

AVIONICS MASTER SWITCH FAILED IN FLIGHT. AIRCRAFT LANDED WITH NO FURTHER DIFFICULTIES. MAINTENANCE REMOVED AND REPLACED THE AVIONICS MASTER SWITCH IAW AIRCRAFT MM.

Part: MASTER SWITCH — FAILED (COCKPIT)

AVIONIC SWITCH FAILED MAINTENANCE REPLACED SWITCH AND RETURNED THE AIRCRAFT TO SERVICE.