N809TA
Registered owner: RHOADES AVIATION INC, HI (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
IN FLIGHT, CREW HAD WHEEL WELL OVERHEAT LIGHT AS WELL AS MASTER FIRE WARNING LIGHTS ILLUMINATE. LIGHTS EXTINGUISHED WHEN LANDING GEAR WAS EXTENDED. UPON LANDING, MAINTENANCE INSPECTION DETERMINED OVERHEAT SENSING LOOP CONNECTION WAS DIRTY, CLEANED AND PERFORMED OPERATIONAL CHECK PER AMM- 26-17-00. SYSTEM CHECKED NORMAL. NO FURTHER DEFECTS REPORT AFTER SUBSEQUENT FLIGHTS.
CORROSION WAS FOUND AT LT WING BOTTOM SKIN LOWER SURFACE AT WS 475 TO WS 525.
CORROSION WAS FOUND AT LT WING BOTTOM SKIN LOWER SURFACE AT INBOARD TO WS 195.
EMERGENCY LIGHT INOPERABLE ON FWD ENTRY DOOR AND FWD GALLEY SERVICE DOOR.
CORROSION WAS FOUND AT AT LT WING BOTTOM SKIN LOWER SURFACE AT WS 315 TO WS 475.
EMERGENCY LIGHT INOPERABLE ON FWD ENTRY DOOR AND FWD GALLEY SERVICE DOOR.
CORROSION WAS FOUND AT AFT CARGO FWD BULKHEAD LOWER CHORD AT BS 727 BETWEEN S-25L AND 25R.
CORROSION WAS FOUND AT LT WING LEADING EDGE FRONT SPAR LOWER CHORD HORIZONTAL LEG AT FSS 135.
CORROSION WAS FOUND AT RT WING FRONT SPAR LOWER CHORD AT FSS 416.8.
CORROSION WAS FOUND AT KEEL BEAM LOWER CHORD AT AFT CARGO BS 727 S-27L (LENGTH: 3" WIDTH: 1"). REFER TO NRC CA1174-02-010.
CORROSION WAS FOUND AT RT WING FRONT SPAR LOWER CHORD AT FSS 442.3.
CORROSION WAS FOUND AT FWD & AFT SURFACE OF RT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER LUG.
CORROSION WAS FOUND AT LT WING LEADING EDGE FRONT SPAR LOWER CHORD HORIZONTAL LEG AT FSS 307.
CORROSION WAS FOUND AT LT WING LEADING EDGE FRONT SPAR LOWER CHORD HORIZONTAL LEG AT FSS 422.
DURING A C1 CHECK, FOUND THE LEFT WING UPPER SURFACE WAS CORRODED ON REAR SPAR BETWEEN WS 150 - 205. CORROSION WAS BLENDED OUT BEYOND SRM LIMIT. REPAIRED IAW DOCUMENT ROO3 REV 01.
DURING INSPECTION IAW CARD 53-30-00-101, FOUND FUSELAGE SKIN AT BS 1016 BETWEEN STRINGERS 24R - 25R WAS CORRODED. A REPAIR WAS CARRIED OUT IAW DOCUMENT 2016R002.
DURING A C1 CHECK, IAW TASK CARD 53-30-00-101, FOUND A CRACK ON FUSELAGE SKIN AT BS 937, STRINGER 24L. REPAIRED IAW REPAIR PLAN DOCUMENT 2016R001.
DURING A C1 CHECK, DURING INSPECTION IAW TASK CARD53-88-80-101, FOUND BS 1016 STRINGER 17R FITTING CORRODED. THE STRINGER FITTING WAS REPLACED IAW ENGINEERING AUTHORIZATION B737-53-00-8.