N35084
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.
18 reports on file, 1997-08-29 – 1999-07-08.
Part: BUS BAR — FAILED (COCKPIT)
THE CREW OBSERVED SMOKE IN THE AREA OF THE FIRE T HANDLES ON OVERHEAD CIRCUIT BREAKER PANEL AND JUST TO LEFT OF T HANDLES WHILE EN ROUTE FROM MXP TO EWR. THE EMERGENCY CHECKLIST WAS COMPLETED AND THE AIRCRAFT WAS DIVERTED TO CDG WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND RIGHT EMERGENCY BUS A PHASE B7-48 BUS BAR TERMINAL AND ELECTRICAL FLAG TERMINAL X274AA8A BURNED. THE RIGHT EMERGENCY BUS BAR EPR NR 3 & NR 2 C/B WAS REPLACED. ADDED ONE MORE C/B TO OVERHEAD C/B PANEL F21 AND INSTALLED TWO NEW FLAG TERMINALS TO CONNECT BUS BAR.
Part: SUPPORT BEAM — CORRODED (LAVATORY F)
INSPECTION FOUND LAV F OUTBOARD SUPPORT BEAM CORRODED. A NEW SUPPORT BEAM WAS INSTALLED IAW SRM 51-42-00 AND GMM 10-900-01.
Part: SUPPORT BEAM — CORRODED (LAVATORY F)
INSPECTION FOUND LAV F INBOARD SUPPORT BEAM CORRODED. A NEW SUPPORT BEAM WAS INSTALLED IAW SRM 51-42-00 AND GMM 10-900-01.
Part: SUPPORT BEAM — CORRODED (BS 392-450)
INSPECTION FOUND FLOOR SUPPORT BEAM CORRODED BETWEEN FLOORBOARDS 227CF AND 226AF AT STA 392 TO 450. A NEW SUPPORT BEAM WAS INSTALLED IAW SRM 51-42-00 AND GMM 10-900-01.
Part: SUPPORT BEAM — CORRODED (LAVATORY F)
INSPECTION FOUND LAV F LATERAL SUPPORT BEAM CORRODED. A NEW SUPPORT BEAM WAS INSTALLED IAW SRM 51-42-00 AND GMM 10-900-01.
Part: SUPPORT — CORRODED (BS 1884)
INSPECTION FOUND FLOORBOARD SUPPORTS AT STA 1884 CORRODED. NEW FLOOR SUPPORTS WERE INSTALLED IAW SRM 51-42-00 AND GMM 10-900-01.
Part: SUPPORT BEAM — CORRODED (BS 459)
INSPECTION FOUND FLOOR SUPPORT BEAMS AT STA 459 CORRODED BETWEEN FLOORBOARDS 227CF, 226AF AND 232AF. NEW FLOOR SUPPORT BEAMS WERE INSTALLED IAW SRM 51-42-00 AND GMM 10-900-01.
Part: SUPPORT BEAM — CORRODED (LAVATORY E)
INSPECTION FOUND LAV E INBOARD SUPPORT BEAM CORRODED. A NEW SUPPORT BEAM WAS INSTALLED IAW SRM 51-42-00 AND GMM 10-900-01.
Part: TR UNIT — DELAMINATED (NR 1 ENGINE)
INSPECTION FOUND NR 1 ENGINE O/B TRANSLATING COWL DELAMINATED AT AFT INNER LOWER SECTION. REPAIRED IAW MM 78-32-01.
Earlier reports · 1997–1998 · 9 reports
1998
Part: STIFFENER — CRACKED (LT MLG WW)
INSPECTION FOUND A 2 CRACK ON VERTICAL STIFFENER IN AFT WEB OF LEFT MLG WHEEL WELL. THE STIFFENER WAS REMOVED. A NEW PART WAS FABRICATED AND INSTALLED IAW SRM 51-21-01 AND 51-31-01.
Part: FAIRING — CRACKED (NR 1 PYLON)
INSPECTION FOUND A 2 CRACK IN NR 1 PYLON LT FAIRING. THE FAIRING WAS REMOVED. A NEW FAIRING WAS FABRICATED AND INSTALLED IAW SRM 51-35-02.
Part: ANGLE — CRACKED (NOSE COWL)
INSPECTION FOUND A 2 CRACK IN NR 1 ENGINE NOSE COWL AFT BULKHEAD AND ANGLE SUPPORT. THE ANGLE WAS REMOVED. A NEW ANGLE WAS FABRICATED AND INSTALLED IAW SRM 54-11-01, FIGURE 1 AND 51-31-01.
Part: RIB — CRACKED (NR 1 LE SLAT)
INSPECTION FOUND A 1 CRACK IN OUTBOARD RIB OF NR 1 SLAT. THE RIB WAS REMOVED AND A NEW RIB WAS INSTALLED IAW SRM 51-37-01 AND 51-35-02.
Part: RIB — CRACKED (NR 2 LE SLAT)
INSPECTION FOUND A 1 CRACK IN INBOARD END RIB OF NR 2 SLAT. THE RIB WAS REMOVED AND A NEW RIB WAS INSTALLED IAW SRM 51-31-01.
Part: ANGLE — CORRODED (CARGO DOORWAY)
INSPECTION FOUND MAIN BAGGAGE BIN DOOR JAMB Z-ANGLE CORRODED. THE ANGLE WAS REPAIRED IAW SRM 53-05, FIGURE 63.
Part: BATTERY — DISCHARGED (CABIN)
INSPECTION FOUND FLASHLIGHT AT L-2 DOOR INOPERATIVE. THE FLASHLIGHT BATTERY WAS REPLACED IAW MM 25-60-00.
1997
Part: AIR BOTTLE — BLOWN (R4 DOOR)
THE R-4 DOOR WOULD NOT CLOSE AND ARM. INSPECTION FOUND THE R-4 DOOR ASSIST BOTTLE BLOWN. THE BOTTLE WAS SERVICED AND OPERATION CHECKED GOOD.
Part: BOLT — CRACKED (RT ENGINE COWL)
MAINTENANCE FOUND THE NR 3 ENGINE LEFT CORE COWL MISSING AND EGT STRAKES DAMAGED. THE EGT STRAKES, LEFT AND RIGHT CORE COWLING WERE REPLACED. IN ADDITION, THE NR 4 AND NR 5 CAP STRUTS, LOWER VENT SYSTEM MANIFOLD AND NR 3 ENGINE EXHAUST NOZZLE WERE REPLACED. *S/D* ONLY THE NR 3 ENGINE RT CORE COWL DEPARTED THE AIRCRAFT. INVESTIGATION BY ENGINEERING CONCLUDED THAT ONE OF THE BOLTS HOLDING THE HINGE FITTING ONTO THE PYLON HAD DEVELOPED A CRACK WHICH SLOWLY PROGRESSED UNTIL BOLT SEPARATED. THE REMAINING BOLTS EVENTUALLY SEPARATED DUE TO THE INCREASED LOAD.