N319NE
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| Asia Pacific Airlines | Operator | on 2008-05-16 | Operator named in NTSB report |
Accident & incident history
Operated by Asia Pacific Airlines (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.
14 reports on file, 2009-03-08 – 2015-10-25.
Part: ENGINE — LEAKING (NR 3)
NR 3 ENG EXPERIENCED OIL LOSS. OIL PRESSURE AT APPROX 10 PSI ON IDLE PRIOR TO SHUT DOWN. DUE TO WEATHER ACFT DIVERTED TO ALTERNATE, FLIGHT ARRIVED SAFELY. TROUBLESHOT NR ENG OIL LOSS, ENG INITIALLY HAD APPROX 1 GAL IN THE SYS & SERVICED APPROX 3 GAL FOR TROUBLESHOOTING. FOUND OIL SUPPLY LINE AT 1:00 O CLOCK POSITION OF EXHAUST. REPLACED OIL LINE, INSPECTED MAIN OIL STRAINER FOR CONTAMINATION, NO DEFECT NOTED. RAN ENG, OPERATIONS CHECKED NORMAL, NO VIBRATION NOTED. PERFORMED NORMAL ENG SHUTDOWN. INSPECTED ENG, TAILPIPE NORMAL, OK TO PROCEED.
Part: LINE — UNKNOWN (NR 3 ENGINE)
NUMBER 3 ENG EXPERIENCED OIL LOSS. OIL PRESS AT APPROX 10 PSI ON IDLE PRIOR TO SHUT DOWN. DUE TO WEATHER ACFT DIVERTED TO ALTERNATE, FLIGHT ARRIVED SAFELY. TROUBLESHOOTING IN PROGRESS. ENG HAD APPROX 1 GAL IN THE SYS & SERVICED APPROX 3 GAL. FOUND OIL SUPPLY LINE AT 1 O CLOCK POSITION OF THE EXHAUST. REPLACED OIL LINE, INSPECTED MAIN OIL STRAINER FOR CONTAMINATION, NO DEFECTS NOTED. RAN ENG, OPERATIONS NORMAL, NO VIBRATION NOTED. PERFORMED NORMAL ENG SHUT DOWN. INSPECTED ENG TAIL PIPE, NORMAL. OK TO PROCEED.
Earlier reports · 2009–2013 · 12 reports
2013
Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 69,196 hrs · 29,471 cycles
8C CHECK. DURING CPCP INSPECTION, PERFORMED VISUAL INSPECTION AND FOUND LEVEL 2 CORROSION ON LOWER ANGLE OF BS 950 CANTED BULKHEAD BETWEEN S22-23L. BLENDED OUT CORROSION, PENETRATION DEPTH WAS OVER LIMITS IAW SRM 53-10-1, FIG 1.
Part: BULKHEAD — CORRODED (ZONE 100) · corrosion level 2 · airframe 69,196 hrs · 29,471 cycles
8C CHECK. DURING CPCP INSPECTION, CORROSION WAS FOUND. THE CORROSION DAMAGE THROUGH THE PART ON THE NOSE WHEEL WELL BS 294.5 BULKHEAD WEB.
Part: SKIN — CORRODED (ZONE 600) · corrosion level 2 · airframe 69,196 hrs · 29,471 cycles
8C CHECKK. DURING PERFORMED CPCP INSPECTION, CORROSION WAS FOUND ON THE UPPER SKIN UPPER SURFACE OF THE WING CENTER SECTION, AT BS 783.95, BETWEEN RBL 63.0 AND RBL 65.5. CORROSION BLENDED OUT. THE DAMAGE CONDITION HAD EXCEEDED THE ALLOWABLE LIMITATION IAW SRM 57-30-1, FIG 4.
2011
Part: BEAM — CORRODED (HORIZ STAB) · corrosion level 2 · airframe 68,255 hrs · 29,172 cycles
DURING PERFORM THE MAINTENANCE WORK (7C CHECK CARD NO.:C53-300-10 PART 1 OF 2), CORROSION WAS FOUND ON THE AFTER FLANGE OF THE LT HORIZONTAL STABILIZER T/E LOWER BEAM AT ELEV STA 156~160 AND ELEV STA 186.5~190. THE DEPTH AFTER BLENDOUT IS OUT OF LIMIT. THE APPROVED REPAIR DATA (FAA FORM 8110-3) HAS BEEN RECEIVED FROM DER ON SEP 19, 2011.
2010
Part: SPAR — CRACKED (LT WING) · corrosion level 2 · airframe 67,306 hrs · 28,869 cycles
ACFT INPUT FOR 6C CHK ON DEC 10, 2009. DURING CPCP INSP, THE INSPECTOR PERFORMED VISUAL INSP AND FOUND LEVEL 2 CORROSION ON LT WING FRONT SPAR WEB BETWEEN WS 508 AND WS 517; LENGTH:3.75"; WIDTH:2.5"; THICKNESS OF ORIGINAL: 0.370"; THICKNESS OF CORROSION REMOVED: 0.272" . AFTER (OWNER) VERIFIED AS MAJOR REPAIR ON JAN 29, 2010, THE SPAR WEB CORROSION HAS BEEN REPAIRED IAW FAA DER APPROVED DATA AND FORM 337 ALSO SUBMITTED TO FAA FOR FINAL RESULT OF CORRECTIVE ACTION DETAIL.
Part: SKIN — CORRODED (BS 620 S26R) · corrosion level 2 · airframe 67,306 hrs · 28,869 cycles
DURING CPCP, THE INSPECTOR PERFORMED VISUAL INSPECTION AND FOUND LEVEL 2 CORROSION ON SKIN OF FWD CARGO DOOR CUTOUT AFT LOWER CORNER STA: BS 620 S26R. AFTER APA (OWNER) VERIFY AS A MAJOR REPAIR ON JAN 29, 2010, THE SKIN CORROSION HAS BEEN REPAIRED IAW FAA DER APPROVED DATA AND FORM 337 WILL BE SUBMITTED TO FAA FOR FINAL RESULT OF CORRECTIVE ACTION DETAIL.
Part: SKIN — CORRODED (BS 620 S26R) · corrosion level 2
DURING CPCP, THE INSPECTOR PERFORMED VISUAL INSPECTION AND FOUND LEVEL 2 CORROSION ON SKIN OF FWD CARGO DOOR CUTOUT AFT LOWER CORNER STA: BS620 S26R. AFTER APA (OWNER) VERIFY AS A MAJOR REPAIR ON JAN 29, 2010, THE SKIN CORROSION HAS BEEN REPAIRED IAW DER APPROVED DATA AND FORM 337 WILL BE SUBMITTED TO FAA FOR FINAL RESULT OF CORRECTIVE ACTION DETAIL.
Part: SPAR — CORRODED (RT WING) · corrosion level 2
THE ACFT INPUT FOR 6C CHK ON DEC 10, 2009. DURING VISUAL INSP BY INSPECTOR, THE LEVEL 2 CORROSION WAS FOUND ON RT WING FRONT SPAR LOWER CHORD AT WS 727.5. THE CHORD THICKNESS OF ORIGINAL IS 0.103". THE CHORD THICKNESS OF CORROSION REMOVED IS 0.040". PHOTO WILL BE SENT BY E-MAIL. AFTER (OWNER) VERIFY AS A MAJOR REPAIR ON JAN 29, 2010, THE SPAR LOWER CHORD HAS BEEN REPAIRED IAW FAA DER APPROVED DATA AND FORM 337 WILL BE SUBMITTED TO FAA FOR FINAL RESULT OF CORRECTIVE ACTION DETAIL.
Part: SPAR — CORRODED (RT WING) · corrosion level 2
THE ACFT INPUT FOR 6C CHECK ON DEC 10, 2009. DURING CPCP INSP, THE INSPECTOR PERFORMED VISUAL INSP AND FOUND LEVEL 2 CORROSION ON RT WING FRONT SPAR LOWER CHORD AT WS 727.5. THE CHORD THICKNESS OF ORIGINAL IS 0.103". THE THICKNESS OF CORROSION REMOVED IS 0.040". AFTER (OWNER) VERIFIED AS MAJOR REPAIR ON JAN 29, 2010, THE SPAR LOWER CHORD CORROSION HAS BEEN REPAIRED.
Part: SPAR — CORRODED (LT WING) · corrosion level 2 · airframe 67,306 hrs · 28,869 cycles
THE ACFT INPUT FOR 6C CHK ON DEC 10, 2009. DURING CPCP, THE INSPECTOR PERFORMED VISUAL INSP AND FOUND LEVEL 2 CORROSION ON LT WING FRONT SPAR WEB BETWEEN WS 508 AND WS 517; LENGTH:3.75"; WIDTH:2.5"; THICKNESS OF ORIGINAL:0.370"; THICKNESS OF CORROSION REMOVED:0.272". AFTER (OWNER) VERIFY AS A MAJOR REPAIR ON JAN 29, 2010, THE SPAR WEB CORROSION HAS BEEN REPAIRED IAW FAA DER APPROVED DATA AND FORM 337 WILL BE SUBMITTED TO FAA FOR FINAL RESULT OF CORRECTIVE ACTION DETAIL.
2009
Part: SPAR — CORRODED (RT WING) · airframe 67,306 hrs · 28,869 cycles
DURING CPCP, THE INSPECTOR PERFORMED VISUAL INSPECTION AND FOUND CORROSION ON RT WING FRONT SPART LOWER CHORD PLATE AT WS 482. AFTER REPAIRING TO THE FRON SPAR LOWER CHORD PLATE, FORM 337 WILL BE SUBMITTED TO FAA FOR FINAL RESULT OF CORRECTIVE ACTIONS DETAIL.
Part: TRANSCEIVER — MALFUNCTIONED (HF SYSTEM) · airframe 66,441 hrs · 28,580 cycles
AIRCRAFT, AIR RETURNED DUE TO NR 1 AND NR 2 HF'S WOULD NOT TRANSMIT OR RECEIVE. CLEANED AND RESEATED BOTH TRANSCEIVERS, OPS CHECK WITH SFO NORMAL. OK FOR SERVICE NO FURTHER PROBLEMS