N505
Registered owner: WHEELER JARED L, AZ (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
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.
5 reports on file, 2016-06-17 – 2022-01-23.
Part: NONE — NONE · airframe 78,180 hrs · 29,405 cycles
DURING HEAVY MAINTENACE, CRACK EMERGENCY EXIT DOOR 834 AFT FRAME SEGMENT 1 IN PASSENGER (1EA) (CRACK LENGTH:2.300 INCH); REF AEROMAN N/R 2021-491638, REPLACED SEGMENT (2EA), BEAM (3EA) AND FASTENER LOC ON EMERGENCY EXIT DOOR 843 PASSENGER CABIN IAW SRM A320 51-42-11, THIS JOB WAS DOCUMENTED ON JOB CARD A320-52-1144-02-JB, EC A320-52-1144, MAJOR REPAIR
Part: CONNECTING ROD — BROKEN (ENGINE) · airframe 2,600 hrs
THE ENGINE WAS ORIGINAL 1979. IT SUFFERED A PROPELLER STRIKE/SUDDEN STOPPAGE EVENT IN JANUARY 1996. THE CRANKSHAFT WAS BENT BEYOND LIMITS. THE CRANKSHAFT AND CASE WERE REPLACED WITH SERVICEABLE PARTS GROUND .006 OVER. ON 12/21/16, THE ENGINE FAILED IN FLIGHT AND THE AIRCRAFT WAS LANDED AT AN AIRPORT UNEVENTFULLY. THE NUMBER 4 CONNECTING ROD FAILED AND PUNCHED A HOLE IN THE ENGINE CASE. THERE WAS NO EVIDENCE THAT THE CONNECTING RODS WERE MAGNAFLUXED NOR CHECKED FOR PARALLEL. THIS REQUIREMENT WASN'T ADDED TO THE LYCOMING ICAS UNTIL YEARS LATER VIA SB 533. THE AIRCRAFT RECORDS DO NOT INDICATE THAT THE CONNECTING RODS HAD EVER BEEN REPLACED. THIS ENGINE WAS FLOWN 600 HOURS PAST THE MANUFACTURER'S RECOMMENDED TBO OF 2000 HOURS. THE ENGINE WAS ALSO 25 YEARS PAST IT'S RECOMMENDED 12 YEAR TBO. THE ROOT CAUSE OF THE ENGINE FAILURE WAS DETERMINED TO BE CONNECTING ROD FAILURE OF THE NUMBER 4 CYLINDER.
Part: DOOR SILL — CORRODED (FUSELAGE) · airframe 34,512 hrs · 24,379 cycles
AFT CARGO DOOR CUTOUT FLOORSILL HAS MULTIPLE AREAS OF CORROSION.
Part: ANGLE — CORRODED (FUSELAGE) · airframe 34,512 hrs · 24,379 cycles
PAX DOOR LOWER SURROUND STRUCTURE, CAP ANGLES ARE CORRODED, PN SH670-31825-9 AND SH670-31821-5.
Part: STIFFENER — CRACKED (FUSELAGE) · airframe 34,512 hrs · 24,379 cycles
FS 202.75, FWD SIDE OF BULKHEAD, LBL 30.0 STIFFENER HAS AN INDICATION .15" LONG AT THE UPPER EDGE OF FLANGE.