N408PE
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| CONTINENTAL AIRLINES INC | Operator | on 1994-02-09 | Operator named in NTSB report |
Accident & incident history
Operated by CONTINENTAL AIRLINES, INC. (per NTSB report)
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.
22 reports on file, 1996-07-04 – 1997-09-01.
Part: ENGINE — FAILED (NR 1)
SPARKS WERE REPORTED COMING FROM THE NR 1 ENGINE EXHAUST WHILE IN FLIGHT. THE AIRCRAFT WAS RETURNED TO EWR WHERE IT LANDED WITHOUT INCIDENT. THE NR 1 ENGINE WAS REMOVED AND REPLACED AND OPERATIONAL CHECKS WERE GOOD.
Part: ANGLE — CORRODED (BS 267)
INSPECTION FOUND VERTICAL AND HORIZONTAL SUPPORT ANGLES FOR RT UPPER STRUT AND FLOORBEAM CORRODED AT STA 267. THE CORRODED AREA WAS CUT OUT, DOUBLERS, FILLER, AND A SUPPORT WERE FABRICATED AND INSTALLED IAW SRM 51-10-2, 51-40-4, AND 51-30-2.
Part: FRAME — CRACKED (BS 827)
INSPECTION FOUND FIVE EACH CRACKS IN AFT CARGO DOOR FRAME AT BS 827, STRINGER 23R. THE CRACKS WERE 1 TO 2.5 INCHES LONG. THE FRAME WAS REPAIRED IAW SRM 53-10-4 AND 51-10-2.
Part: STRINGER — CRACKED (RT WING)
INSPECTION FOUND CRACKS TOTALING 4 INCHES IN LENGTH IN RT WING STRINGER 13, AT WBL 135. REPAIR ANGLES WERE REMOVED AND THE CRACKS WERE STOP DRILLED. THE REPAIR ANGLES WERE REINSTALLED IAW SRM 51-10-2 AND BOEING DRAWING 65C34533.
Part: ANGLE — CRACKED (BS 267)
INSPECTION FOUND A 1 INCH CRACK IN RT UPPER CORNER OF NOSE WHEEL WELL ANGLE AT STA 267. A REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-30-0, 51-10-2, AND ECRA 5340-01300.
Part: STRINGER — CRACKED (RT WING)
INSPECTION FOUND A 5 INCH CRACK IN RT WING STRINGER 13 AT WBL 80. THE STRINGER WAS REPAIRED IAW ECRA 5710-01815.
Part: SKIN — CRACKED (BS 947)
INSPECTION FOUND A 2 INCH CRACK IN FUSELAGE SKIN AT UPPER FORWARD CORNER OF L-2 DOOR AT STA 947, S7L. THE CRACKED AREA WAS CUT OUT, A DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW ECRA 5310-03510 AND SRM 53-30-3.
Part: SKIN — CRACKED (BS 283)
INSPECTION FOUND .5 INCH CRACKS AND CORROSION IN FUSELAGE SKIN AT STA 283, S10R. THE CORROSION WAS REMOVED AND THE CRACKED AREA OF SKIN WAS CUT OUT, A REPAIR WAS INSTALLED IAW ECRA 5330-02543.
Part: SKIN — CRACKED (BS 986)
INSPECTION FOUND A 1 INCH CRACK IN FUSELAGE SKIN AT AFT UPPER CORNER OF L-2 DOOR, STA 986, S7L. THE CRACK WAS ROUTED OUT, DOUBLER AND FILLERS WERE FABRICATED AND INSTALLED IAW ECRA 5310-03510, SRM 51-30-2, AND BOEING DRAWING 65C35747.
Part: BATTERY PACK — DISCHARGED (CABIN)
THE L-1 DOOR EXTERIOR EXIT LIGHT FAILED CAPACITY CHECK. THE BATTERY PACK WAS REMOVED, RECHARGED, AND REINSTALLED IAW MM 33-51-71, 33-50-42, AND 33-51-31.
Part: BATTERY PACK — DISCHARGED (CABIN)
THE R-2 DOOR PORTABLE EXIT LIGHT FAILED CAPACITY CHECK. THE BATTERY PACK WAS REMOVED, RECHARGED, AND REINSTALLED IAW MM 33-50-42 AND 33-51-101.
Part: BATTERY PACK — DISCHARGED (CABIN)
THE LT ESCAPE HATCH PORTABLE EXIT LIGHT FAILED CAPACITY CHECK. THE BATTERY PACK WAS REMOVED, RECHARGED, AND REINSTALLED IAW MM 33-50-42 AND 33-51-101.
Part: BATTERY PACK — DISCHARGED (CABIN)
THE R-2 DOOR EXTERIOR EXIT LIGHT FAILED CAPACITY CHECK. THE BATTERY PACK WAS REMOVED, RECHARGED, AND REINSTALLED IAW MM 33-51-71, 33-50-42, AND 33-51-31.
Part: BATTERY PACK — DISCHARGED (CABIN)
THE R-1 DOOR PORTABLE EXIT LIGHT FAILED CAPACITY CHECK. THE BATTERY PACK WAS REMOVED, RECHARGED, AND REINSTALLED IAW MM 33-51-42 AND 33-51-101.
Earlier reports · 1996 · 8 reports
1996
Part: SKIN — CRACKED (C 2 DOOR)
INSPECTION FOUND A .5 INCH CRACK AT LIGHTENING HOLE OF C-2 DOOR INTERIOR SKIN. THE CRACK WAS STOP DRILLED, A WEB REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-10-1, 51-10-2, 51-30-2 AND 51-40-2.
Part: STIFFENER — DAMAGED (WS 180.36)
TWO STIFFENERS AND AFT SIDE OF WEB ON RT WING AT STA 180.36 SUSTAINED DAMAGE FROM TOOLING. THE STIFFENERS WERE REMOVED AND THE DAMAGED AREA WAS BLENDED IAW SRM 51-30-2 AND 57-10-1. STIFFENERS AND REPAIR PLATES WERE FABRICATED AND INSTALLED IAW SRM 57-10-2 ANS 57-10-6.
Part: SKIN — CORRODED (BS 312-328)
INSPECTION FOUND LOWER FUSELAGE SKIN AND STRINGER CORRODED WITH RIVETS POPPED AT STA 312 TO 328, STRINGER 27L TO 26R. THE CORRODED AREA OF SKIN WAS CUT OUT, A REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-30-2. STRINGER 28 WAS REMOVED AND REPLACED IAW SRM 53-30-2 AND 51-30-2.
Part: STIFFENER — CRACKED (RT WING)
INSPECTION FOUND A .25 INCH CRACK IN RT WING VERTICAL STIFFENER AT LEADING EDGE UNDER PANEL 6526. THE STIFFENER WAS REMOVED AND REPLACED IAW SRM 51-30-2 AND 51-10-5.
Part: SKIN — CRACKED (BS 277)
INSPECTION FOUND A 2 INCH CRACK IN FUSELAGE SKIN AT STA 277, STRINGER 26R. THE CRACKED AREA WAS CUT OUT, A REPAIR DOUBLER AND FILLER WERE FABRICATED AND INSTALLED IAW SRM 53-30-2, 53-30-3 AND 51-10-2.
Part: FLOOR BEAM — CRACKED (BS 660)
INSPECTION FOUND A .5 INCH CRACK IN FLOOR BEAM UPPER CHORD AT STA 660, BL 07. THE FLOORBEAM WAS REPAIRED IAW EA 5710-01322, OPERATION 2 AND ECRA 5710-01743.
Part: SKIN — CRACKED (RT WING)
INSPECTION FOUND TWO .25 INCH CRACKS IN RT WING LEADING EDGE SKIN AT ANTI-ICE DUCT CUTOUT, NR 5 SLAT. THE CRACKED AREA WAS CUT OUT, REPAIR PARTS WERE FABRICATED AND INSTALLED IAW SRM 57-30-4 AND 51-10-2.
Part: SKIN — DENTED (BS 400)
INSPECTION FOUND A DENT IN FUSELAGE SKIN AT STA 400, S18L. THE DENTED AREA WAS CUT OUT, A REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-30-3 AND 51-10-2.