N751CA

Part: STRAP — CORRODED (ZONE 600) · airframe 21,999 hrs · 16,304 cycles

DURING MAINTENANCE AN AREA OF CORROSION WAS VISUALLY IDENTIFIED ON THE RH SPAR STRAP. (SK 402-47B). THIS CORROSION MEASURES APPROXIMATELY 1.182 INCHES LONG, .815 INCHES WIDE, AND .050 INCHES DEEP LOCATED AT APPROXIMATE RWS 125.54. THIS STRAP WILL BE REMOVED AND REPLACED USING NEW PARTS.

Part: AXLE — CRACKED (RT MLG) · airframe 20,990 hrs · 13,950 cycles

THE PILOT REPORTED THAT DURING A TURN ONTO THE RUNWAY THE AIRCRAFT THE WING DROPPED AND THE AIRCRAFT WOULD NOT ROLL. THE RIGHT TIRE WAS FOUND TO BE LEANING AGAINST THE STRUT. MAINTENANCE INSPECTED AND FOUND THE RIGHT AXLE TO BE CRACKED. REMOVED AND REPLACED THE RIGHT LOWER BARREL AND AXLE ASSEMBLY. NO FURTHER DEFECTS NOTED.

Part: CYLINDER — FAILED (NR 1) · airframe 20,747 hrs

PILOT REPORTED A STRONG VIBRATION IN FLIGHT. MAINTENANCE INSPECTED AND FOUND THE LEFT ENGINE #1 CYLINDER TO HAVE LOW COMPRESSION AND THE #3 AND #4 CYLINDERS TO HAVE DAMAGE AT THE ROTOCOIL. ALL THREE CYLINDERS WERE REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: CYLINDER — DAMAGED (NR 4) · airframe 20,747 hrs

PILOT REPORTED A STRONG VIBRATION IN FLIGHT. MAINTENANCE INSPECTED AND FOUND THE LEFT ENGINE #1 CYLINDER TO HAVE LOW COMPRESSION AND THE #3 AND #4 CYLINDERS TO HAVE DAMAGE AT THE ROTOCOIL. ALL THREE CYLINDERS WERE REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: CYLINDER — DAMAGED (NR 3) · airframe 20,747 hrs

PILOT REPORTED A STRONG VIBRATION IN FLIGHT. MAINTENANCE INSPECTED AND FOUND THE LEFT ENGINE #1 CYLINDER TO HAVE LOW COMPRESSION AND THE #3 AND #4 CYLINDERS TO HAVE DAMAGE AT THE ROTOCOIL. ALL THREE CYLINDERS WERE REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: CYLINDER — DAMAGED (NR 3) · airframe 20,335 hrs · 12,433 cycles

PILOT REPORTED RIGHT ENGINE MANIFOLD PRESSURE DROPPED TO 20". AFTER FULL POWER WAS APPLIED THE RIGHT ENGINE STARTED TO SURGE. MAINTENANCE INSPECTED AND FOUND DAMAGE AND DEBRIS IN THE 1,3 & 5 CYLINDERS, FURTHER INVESTIGATION SHOWED METAL SHAVINGS IN THE OIL SUMP & OIL FILTER. THIS APPEARS TO BE A PRE-IGNITION EVENT IN CYLINDER #3. THE ENGINE IS BEING REPLACED - FURTHER DETAILS AVAILABLE UPON TEARDOWN.

Part: O-RING — DETERIORATED (FUEL FILTER) · airframe 20,133 hrs

PILOT REPORTED A FUEL ODOR DURING FLIGHT, IN THE CABIN. MAINTENANCE INSPECTED AND FOUND THE LEFT FUEL FILTER BOWL TO BE LEAKING. THE FUEL BOWL SEALS WERE REPLACED WITH NO FURTHER DISCREPANCIES NOTED.

Part: CROSSBEAM — CRACKED (ZONE 400) · airframe 19,166 hrs · 10,103 cycles

A CRACK WAS DISCOVERED IN THE CROSSBEAM ON THE AFT LEFT SIDE, AROUND ONE OF THE TURBO BRACKET MOUNTING HOLES. THE CRACK MEASURED 1.304 INCHES IN LENGTH. THE TURBO BRACKET WAS INSTALLED TO CHECK FOR PRELOADING. NO PRELOADING WAS NOTED. BEAM WAS REPLACED.

Part: ATTACH FITTING — CRACKED (LT WING) · airframe 19,166 hrs · 10,103 cycles

WHILE PREFORMING OTHER MAINTENANCE IN THE IMMEDIATE AREA, A CRACK WAS NOTED LENGTH WISE ALONG THE RADIUS OF THE FORWARD LOWER, OUTBOARD AFT SIDE WING FITTING (SEE ATTACHMENT FOR PICTURES AND DIMENSIONS.) A .065 THICK SHIM WAS INSTALLED BETWEEN THE LOWER HORIZONTAL FACE OF THE FITTING, AND THE UPPER HORIZONTAL FACE OF THE SPAR CAP. UPON FASTENER REMOVAL, THE INBOARD PORTION OF THE FITTING "RELAXED" OFF THE SHIM, LEAVING A GAP BETWEEN THE FITTING AND THE SHIM. IT IS POSSIBLE THAT UPON PREVIOUS INSTALLATION, THE HORIZONTAL LEG OF THE FITTING WAS DRAWN DOWN TOO TIGHT TO CLOSE THE GAP WITH THE SHIM, THEREFORE STRESSING THE FITTING, SPECIFICALLY THE RADIUS PORTION. A THOROUGH RECORDS REVIEW WAS COMPLETED TO REVIEW OF ANY MAINTENANCE THAT MAY HAVE BEEN PERFORMED ON THE FITTING. NO ENTRIES WERE FOUND. WE ALSO CONTACTED MANUFACTURER. THEY ARE CURRENTLY REVIEWING THEIR PRODUCTION INSPECTION RECORDS OF THIS AIRCRAFT FOR ANY DATA. THE OPERATORS INSPECTION PROGRAM PRESCRIBES A DETAILED VISUAL INSPECTION OF THESE AREAS EACH 180 HOUR OF OPERATION. DETAILS OF THIS INSPECTION FINDING WILL BE SHARED WITH ALL MAINTENANCE TECHNICIANS FOR AWARENESS.

Part: EXHAUST VALVE — DAMAGED (NR 6 CYLINDER) · airframe 18,458 hrs

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

Part: EXHAUST VALVE — DAMAGED (NR 4 CYLINDER) · airframe 18,406 hrs

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

Part: EXHAUST VALVE — DAMAGED (NR 6 CYLINDER) · airframe 18,307 hrs

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

Part: EXHAUST VALVE — DAMAGED (NR 3 CYLINDER) · airframe 18,307 hrs

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

Part: EXHAUST VALVE — DAMAGED (NR 2 CYLINDER) · airframe 18,307 hrs

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

Part: EXHAUST VALVE — DAMAGED (NR 4 CYLINDER) · airframe 18,307 hrs

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

Part: PACKING — DEFECTIVE (MASTER CYLINDER) · airframe 17,858 hrs · 7,386 cycles

PILOT REPORTED RT BRAKE TEMP FAIL. INSPECTED BRAKE SYS & FOUND RT BRAKE SPONGY. REPACKED THE RT BRAKE MASTER CYLINDER, BLED & SERVICES. AS PRECAUTION, INSPECTED HYD LINES, BRAKE CALIPER & BRAKE LININGS. NO DISCREPANCY OR LEAK NOTED AT THIS TIME.

Part: CALIPER — LEAKING (RT BRAKE) · airframe 17,638 hrs · 6,986 cycles

THE RT BRAKE INOPERATIVE. INSPECTED THE RT BRAKE & FOUND THE CALIPER LEAKING. R & R THE RT CALIPER & BLED RT BRAKE SYS. OPERATIONAL & LEAK CHECKED GOOD.

Part: DRAG BRACE — CRACKED (NLG) · airframe 14,661 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: TARGET — LOOSE (LT MLG)

LEFT HAND MLG DISAGREE WARNING AFTER TAKEOFF. TIGHTENED LOOSE UPLOCK PROXIMITY SENSOR TARGET.