N73380
Registered owner: BANK OF UTAH TRUSTEE, UT (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.
14 reports on file, 2000-02-07 – 2001-01-15.
Part: BRACKET — CRACKED (FUSELAGE) · airframe 18,696 hrs · 10,149 cycles
INSPECTION FOUND A 1 INCH CRACK IN FORWARD BAGGAGE BIN ANGLE BRACKET AT STA 380, S26L. THE ANGLE BRACKET WAS REMOVED AND REPLACED IAW SRM 51-10-02.
Earlier reports · 2000 · 13 reports
2000
Part: SKIN — DENTED (CARGO DOOR) · airframe 18,413 hrs · 10,001 cycles
INSPECTION FOUND AFT CARGO DOOR SKIN DENTED. THE DENTED AREA WAS REMOVED AND A REPAIR WAS INSTALLED IAW SRM 52-00-01, FIGURE 203.
Part: WEB — CRACKED (FUSLEAGE) · airframe 18,413 hrs · 10,001 cycles
INSPECTION FOUND C-2 DOOR AFT CUTOUT LOWER CLOSEOUT WEB BENT AND CRACKED AT STA 847, RBL 26. THE WEB WAS REMOVED AND REPLACED IAW SRM 51-10-02.
Part: WEB — WORN (FUSELAGE) · airframe 18,413 hrs · 10,001 cycles
INSPECTION FOUND C-2 DOOR FORWARD CUTOUT LOWER CLOSEOUT WEB BENT, WORN, AND DISTORTED AT STA 787, RBL 26. REPAIRED IAW SRM 51-70-13.
Part: ANGLE — CORRODED (FUSELAGE) · airframe 18,413 hrs · 10,001 cycles
INSPECTION FOUND RT Z-ANGLE CORRODED AT STA 993.THE ANGLE WAS REMOVED AND A NEW ANGLE WAS INSTALLED IAW SRM 53-60-51, FIGURE 1.
Part: PANEL — CORRODED (FUSELAGE) · airframe 18,413 hrs · 10,001 cycles
INSPECTION FOUND TRANSITION PANEL ON LT SIDE OF AFT BAG BIN CORRODED AT STA 807-867. THE PANEL WAS REMOVED AND REPLACED IAW SRM 53-60-53.
Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 18,413 hrs · 10,001 cycles
INSPECTION FOUND SEVERAL CRACKS IN INTERCOSTAL BETWEEN FLOORBEAMS AT STA 380-400. THE CRACKS WERE APPROXIMATELY TWO INCHES LONG. THE INTERCOSTAL WAS REMOVED AND REPLACED IAW SRM 51-40-02.
Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 18,413 hrs · 10,001 cycles
INSPECTION FOUND FLOORBEAM CORRODED AROUND FASTENER HOLE AT STA 986, RBL 29. REPAIRED IAW SRM 53-00-51, PAGE 214.
Part: ANGLE — CRACKED (STA 540) · airframe 18,413 hrs · 10,001 cycles
INSPECTION FOUND A 4" CRACK IN R/H RAM AIR DUCT SUPPORT ANGLE JUST FORWARD OF DUCT AT DOOR, STA 540. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-10-02.
Part: ANGLE — CRACKED (TE FLAP) · airframe 18,413 hrs · 10,001 cycles
INSPECTION FOUND A 1/2 INCH CRACK IN UPPER SKIN ATTACH ANGLE AT O/B SIDE OF NR 6 FLAP TRACK FAIRING, WBL 203. THE ATTACH ANGLE WAS REMOVED AND REPLACED IAW SRM 51-40-02.
Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 18,413 hrs · 10,001 cycles
INSPECTION FOUND CORROSION AROUND FASTENER HOLE ON FLOORBEAM UPPER CHORD AT STA 344, LBL 21 AND LBL 42. REPAIR STRAPS WERE INSTALLED AT EACH LOCATION IAW SRM 53-00-51.
Part: PANEL — CORRODED (FUSELAGE) · airframe 18,413 hrs · 10,001 cycles
INSPECTION FOUND LT TRANSITION PANELS IN AFT BAG BIN CORRODED AT STA 727-727D AND AT 727D-807. THE PANELS WERE REPLACED IAW SRM 53-60-53 AND 51-10-02.
Part: SKIN — PUNCTURED (FUSELAGE) · airframe 18,413 hrs · 10,001 cycles
INSPECTION FOUND RT FUSELAGE SKIN PUNCTURED AT STA 270, STRINGER 18R. A REPAIR WAS INSTALLED IAW SRM 53-00-01, 51-20-05, AND 51-21. A DIP WAS ISSUED TO REINSPECT AREA FOR PULLED/LOOSE RIVETS EVERY 2500 FLIGHTS AND TO INSTALL A FLUSH REPAIR BY 20,000 FLIGHTS OR 1/4 D CHECK.
Part: SEAL — SEPARATED (NR 1 ENGINE) · airframe 15,948 hrs · 8,680 cycles
SMOKE ENTERED THE COCKPIT AND CABIN ON TAKEOFF FROM EWR. ALL ENGINE INDICATIONS WERE NORMAL. ALL CHECK LISTS WERE COMPLIED WITH AND THE AIRCRAFT WAS RETURNED TO EWR WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THAT THE NR 1 ENGINE WAS LEAKING OIL INTO THE BLEED SYSTEM. THE NR 1 ENGINE WAS REMOVED AND REPLACED. A FULL BURNOUT OF THE LEFT AIR CONDITIONING SYSTEM WAS PERFORMED IAW MM 21-00-01, PAGES 101-108. NO FURTHER SMOKE WAS NOTED. THE LT COALESCER BAG WAS REPLACED AND LEAK CHECK OF THE LT PACK WAS GOOD. THE NR 1 ENGINE WAS RUN AND ALL TESTS WERE GOOD. *S/D* INVESTIGATION REVEALED THAT THE PRIMARY CAUSE OF FAILURE WAS DUE TO SEPARATION OF THE NR 3 AFT AIR/OIL SEAL.