N751CA
Registered owner: HYANNIS AIR SERVICE INC, MA (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| HYANNIS AIR SERVICE INC. (HYIA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
PILOT REPORTED A BURNING SMELL AFTER TAKE-OFF. MAINTENANCE INSPECTED AND FOUND THE WEATHER RADAR DISPLAY TO BE AT FAULT. THE DISPLAY WAS REPLACED WITH NO FURTHER DEFECTS NOTED.
PILOT REPORTED BURNING ELECTRICAL SMELL AFTER TAKE OFF. MAINTENANCE INSPECTED AND FOUND THE INSTRUMENT FAN HARD TO TURN. MAINTENANCE REPLACED THE FAN WITH NO FURTHER DEFECTS NOTED.
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.
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.
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.
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.
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.
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.
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.
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.
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.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
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.
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.
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.
LEFT HAND MLG DISAGREE WARNING AFTER TAKEOFF. TIGHTENED LOOSE UPLOCK PROXIMITY SENSOR TARGET.