N2651S
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
Maintenance disclosures
DURING MAINTENANCE A CRACK WAS VISUALLY IDENTIFIED ON THE AFT SIDE OF THE LEFT NACELLE CROSSOVER BEAM (P/N: 5654104-11). THIS CRACK MEASURES APPROXIMATELY 1.25 INCHES IN LENGTH, AND BEGINS AT THE TOP INBOARD TURBO BRACKET MOUNTING HOLE ON THE AFT FACE OF THE BEAM. THIS CRACK IS CONSISTENT WITH OTHERS FOUND IN THIS AREA AND IS NOT VISIBLE WITH THE TURBO MOUNTING BRACKET INSTALLED. THIS BEAM WILL BE REMOVED AND REPLACED USING NEW PARTS.
PILOT REPORTED RIGHT PROP WENT ALL THE WAY TO THE DETENTE AT CLIMB POWER BUT NEVER CAME BELOW 2700 RPM. MAINTENANCE INSPECTED AND FOUND THE RIGHT PROP GOVERNOR UNABLE TO REGULATE HIGH SPEED RPM. REPLACED PROP GOVERNOR WITH NO FURTHER DEFECTS.
PILOT REPORTED RIGHT MANIFOLD PRESSURE DROPPED TO 25 INCHES AND RIGHT OIL PRESSURE TO JUST ABOVE RED LINE. MAINTENANCE INSPECTED AND FOUND METAL PARTICLES IN THE OIL FILTER. THE ENGINE WAS REPLACED WITH NO FURTHER DEFECTS NOTED. FURTHER DETAILS TO BE PROVIDED UPON ENGINE TEARDOWN INVESTIGATION.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE, AS WELL AS FAULTY PISTON RINGS.
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE, AS WELL AS FAULTY PISTON RINGS.
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.
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.
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.
PILOT REPORTED A FUEL ODOR IN CABIN. ON INSPECTION, FOUND RT SIDE FUEL FILTER BOWL WAS LEAKING. FURTHER EXAMINATION SHOWED THIS TO BE CAUSED BY A BROKEN O-RING WITHIN THE FUEL BOWL. O-RING REPLACED, AND THE UNIT OPERATIONALLY AND LEAK CHECKED GOOD.
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.
CREW REPORTED AVIONICS MASTER SWITCH INOPERATIVE. MX REMOVED AND REPLACED AVIONICS MASTER SWITCH.
UPON INSPECTION, FOUND LT & RT FLAP CABLE ASSEMBLIES TO HAVE BROKEN STRANDS (APPROX 10 TO 15 PERCENT) AT THE POINT WHERE THE CABLE ENTER THE SWEDGED STRAIGHT SHOOK ENDS. NO OTHER AREAS OF THE CABLES SHOWED SIGNS OF BROKEN STRANDS. THE SHANK ENDS WITH BROKEN STRANDS SHOWED SIGNS OF BEING SWEDGED IMPROPERLY, SUGGEST TIME CHANGING FLAP CABLES.
LEFT ENGINE, MECHANIC WAS CHANGING LEAKY PUSHROD TUBE SEALS AND REMOVED LIFTERS TO BLEED OUT OIL. NOTED FACE OF LIFTER TO BE SEVERELY SPALLED. ASSOCIATED CAM LOBE WAS WORN AND STEPPED. REMOVAL OF REMAINING LIFTERS REVEALED VARIED DEGREES OF SPALLING ON ALL INTAKE LIFTERS. NO DAMAGE WAS NOTED ON EXHAUST LIFTERS. ALL INTAKE CAM LOBES SHOWED SIGNS OF WEAR. THERE WERE NO SYMTOMS OF THIS PROBLEM.
RIGHT ENGINE, DAMAGE NOTED TO LEFT ENGINE PROMPTED INSPECTION OF THIS ENGINE. REMOVAL OF LIFTER ASSEMBLIES FROM RANDOM CYLINDERS REVEALED SPALLING TO THE LIFTER FALES AND DAMAGE AND WEAR TO THE ASSOCIATED CAM LOBES. THIS DAMAGE WAS NOTED ON THE INTAKE LIFTERS ONLY.