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
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
15 reports on file, 2001-04-05 – 2026-03-12.
Part: CROSSBEAM — CRACKED (ZONE 400) · airframe 29,104 hrs · 41,233 cycles
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.
Earlier reports · 2001–2019 · 14 reports
2019
Part: GOVERNOR — FAILED (RT PROPELLER) · airframe 24,113 hrs
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.
Part: ENGINE — MAKING METAL (RIGHT) · airframe 24,080 hrs
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.
2016
Part: EXHAUST VALVE — DAMAGED (NR 6 CYLINDER) · airframe 21,303 hrs
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE, AS WELL AS FAULTY PISTON RINGS.
Part: EXHAUST VALVE — DAMAGED (NR 5 CYLINDER) · airframe 21,303 hrs
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE, AS WELL AS FAULTY PISTON RINGS.
Part: EXHAUST VALVE — DAMAGED (NR 6 CYLINDER) · airframe 21,188 hrs
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
Part: EXHAUST VALVE — DAMAGED (NR 4 CYLINDER) · airframe 21,188 hrs
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION. EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
2014
Part: DRAG BRACE — CRACKED (NLG) · airframe 18,017 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.
2012
Part: DRAG BRACE — CRACKED (NLG) · airframe 15,769 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: O-RING — LEAKING (FUEL FILTER) · airframe 15,996 hrs
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.
2011
Part: DRAG BRACE — CRACKED (NLG) · airframe 14,862 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.
2009
Part: MASTER SWITCH — UNSERVICEABLE (COCKPIT) · airframe 13,052 hrs
CREW REPORTED AVIONICS MASTER SWITCH INOPERATIVE. MX REMOVED AND REPLACED AVIONICS MASTER SWITCH.
2002
Part: CONTROL CABLE — BROKEN (TE FLAPS)
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.
2001
Part: LIFTER — SPALLED (LEFT ENGINE)
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.
Part: LIFTER — SPALLED (RT ENGINE)
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.