N1055
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
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.
14 reports on file, 2011-01-28 – 2023-05-17.
Part: TRUNNION — FAILED · airframe 34,824 hrs · 18,387 cycles
PILOT REPORTED RIGHT MAIN LANDING GEAR CAME OUT OF THE AIRCRAFT AFTER LANDING. INITIAL INSPECTION FOUND THE RIGHT MAIN LANDING GEAR TRUNNION FAILED. AIRCRAFT IS UNDER REPAIR.
Earlier reports · 2011–2022 · 13 reports
2022
Part: AXLE — BROKEN (RT MLG) · airframe 34,448 hrs · 17,838 cycles
RIGHT MAIN GEAR AXLE FAILED ON LANDING/TAXI TO GATE. MAINTENANCE IS REPLACING LOWER BARREL & AXLE.
2019
Part: ACTUATOR — BINDING (RUDDER TRIM) · airframe 32,058 hrs
PILOT REPORTED RUDDER TRIM JAMMED IN FLIGHT. MAINTENANCE INSPECTED AND CONFIRMED TRIM WAS DIFFICULT TO ACTUATE. THE RUDDER TRIM TAB ACTUATOR WAS REPLACED, WITH NO ADDITIONAL DEFECTS NOTED. ADDITIONAL DETAILS AVAILABLE UPON TEARDOWN INSPECTION.
2016
Part: EXHAUST VALVE — DAMAGED (NR 1 CYLINDER) · airframe 29,021 hrs
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
Part: EXHAUST VALVE — DAMAGED (NR 1 CYLINDER) · airframe 28,954 hrs
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
Part: EXHAUST VALVE — DAMAGED (NR 6 CYLINDER) · airframe 28,897 hrs
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
Part: EXHAUST VALVE — DAMAGED (NR 4 CYLINDER) · airframe 28,783 hrs
CYLINDER REMOVED DUE TO LOW COMPRESSION AT INSPECTION; EXHAUST VALVE DISPLAYS EVIDENCE OF HEAT DAMAGE.
2015
Part: ENGINE — DAMAGED (RIGHT) · airframe 27,754 hrs · 9,020 cycles
RIGHT ENG OIL PRESS DROPPED TO ZERO IN FLIGHT. DIVERTED & ON SHORT FINAL APPROACH RT ENG STOPPED RUNNING. PROPELLER DID NOT FEATHER. POST LANDING INSPECTION REVEALED OIL LEAKING FROM TOP & BOTTOM OF ENG COWLING. PRELIMINARY EXAMINATION REVEALS TOP OF CRANKCASE BREACHED.
Part: ENGINE — FAILED (RIGHT) · airframe 27,631 hrs · 8,849 cycles
PILOT REPORTED RT ENG FAILED INFLIGHT. R & R THE ENG, OPERATIONAL & LEAK CHECKED GOOD. ENG HAS BEEN SENT FOR TEAR DOWN ANALYSIS.
2014
Part: CALIPER — MISINSTALLED (MLG) · airframe 26,906 hrs · 7,847 cycles
RIGHT MAIN TIRE & GEAR BRAKE CALIPER HAS COME LOOSE & MOVED TO JAM UP ON STRUT. R & R THE RT BRAKE CALIPER, PAD SET & TIRE ASSEMBLY IAW MM CH 32-10-00 WITH NO DEFECTS NOTED. FURTHER INVESTIGATION LEAD TO THE DISCOVERY THAT THE RT MAIN TIRE HAD BEEN CHANGED PREVIOUSLY & THE BRAKE CALIPER WAS NOT PROPERLY INSTALLED. THE RIGHT GEAR LOWER LEG WAS INSPECTED WITH NO DAMAGE FOUND.
2013
Part: SPAR — DAMAGED (FWD CARRY THRU) · airframe 24,737 hrs
DURING A SCHEDULED MX EVENT, DAMAGE WAS NOTED TO THE FORWARD CARRY THROUGH SPAR ASSY IN THE CENTER SECTION. DAMAGE INCLUDES DRILL STARTS TO UPPER CAP AND CORRESPONDING WEB FLANGE CRACKS. THESE DAMAGE POINTS WERE MAPPED AND SUBMITTED FOR ENGINEERING ASSISTANCE. REPAIRS WILL BE CONDUCTED IAW REPAIR DEFINITION SUPPLIED AND SUBSTANTIATED.
Part: SPAR — DAMAGED (AFT CARRY THRU) · airframe 24,737 hrs
DURING A SCHEDULED MX EVENT, DAMAGE WAS NOTED TO THE AFT CARRY THROUGH SPAR ASSY CENTER SECTION. DAMAGE INCLUDES WEB FLANGE CRACKS. OPEN
Part: BEAM — DAMAGED (LT NACELLE) · airframe 24,737 hrs
DURING A SCHEDULED MX EVENT DAMAGE WAS NOTED TO THE LT NACELLE OTBD ENGINE BEAM RADIUS. DAMAGE WAS MAPPED AND SUBMITTED FOR ENGINEERING ASSISTANCE. REPAIRS WILL BE COMPLETED IAW REPAIR DEFINITION SUPPLIED AND SUBSTATIATED.
2011
Part: DRAG BRACE — CRACKED (NLG) · airframe 21,721 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.