N186UA
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| UNITED AIRLINES, INC. (CALA) | Operator | on 1994-02-12 | Operator named in NTSB report |
Accident & incident history
Operated by UNITED 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.
6 reports on file, 1995-05-16 – 1997-02-26.
Part: INFLATION HOSE — LOOSE (SLIDE)
SLIDE/RAFT REMOVED FOR TIME CONTROLLED OVERHAUL. INFLATION HOSES FOUND LOOSE AT ASPIRATOR CONNECTION. SLIDE MAY HAVE NOT INFLATED FULLY IF DEPLOYED. INFLATION HOSES TIGHTENED. THIS IS SECOND INCIDENT OF LOOSE INFLATION HOSES. UNITED WILL CONDUCT A SAMPLE INSPECTION TO DETERMINE THE EXTENT OF THE PROBLEM.
Part: COMPRESSOR — STALLED (NR 3 ENGINE)
NR 3 ENGINE STALLED ON TAKEOFF JUST AFTER LIFTOFF. A/C RETURNED TO FIELD. NO VISIBLE DAMAGE. NO CONTROL SYSTEM FAULTS. SURGE IS ATTRIBUTED TO POOR N2 COMPRESSOR PERFORMANCE. ENGINE TO BE REFURBISHED. ENGINE REPLACED.
Part: BLADE — FAILED (COMPRESSOR)
WHILE IN CRUISE AT FL 370 AND EPR 1.21, STALL CONDITION DEVELOPED. REDUCED THROTTLE AND CONDITION CEASED FOR SHORT TIME, HOWEVER, ENGINE THEN STALLED REPEATEDLY. ENGINE SHUT DOWN. HIGH PRESSURE COMPRESSOR STAGE 5 BLADE FAILED. REPLACED ENGINE. PART TOTAL CYCLES, 388.
Part: PANEL — CRACKED (LT WING LE)
LEFT WING LEADING EDGE FIBERGLASS PANEL WAS FOUND WITH A 35 INCH CRACK. CRACK HAD PROPAGATED FROM AN EXISTING 18 INCH CRACK THAT WAS PREVIOUSLY REPAIRED. PANEL IS LOCATED INBOARD OF THE NR 2 ENGINE. ACCOMPLISHED REPAIR PER GN-MM.
Part: PANEL — CRACKED (LT WING)
ON ARRIVAL TO NRT, THE LEFT WING LEADING EDGE FIBERGLASS PANEL WAS FOUND CRACKED IN TWO PLACES. THE PANEL WAS LOCATED INBOARD OF THE NR 2 ENGINE. CRACK LENGTHS WERE MEASURED TO 18 INCHES AND 5 INCHES. INVESTIGATION FOUND THAT ONLY THE UPPER SKIN WAS AFFECTED. THE HONEYCOMB STRUCTURE WAS NOT AFFECTED. ACCOMPLISHED PERMANENT SKIN REPAIR FOR METAL TO METAL ADHESIVE BONDED ALUMINUM HONEYCOMB PANEL USING VACUUM BAG/HEAT BLANKET PROCESS. PART TOTAL CYCLES, 2,432.
Part: ASPIRATORS — DAMAGED (SLIDE)
AT DISASSEMBLY FOUND SUD SLIDE TURBO-FAN ASPIRATORS WITH BLADE DAMAGE. ADDITIONALLY, THE FLAPPER VALVE ROD FELL OUT. REPLACED 2 EACH TURBO FANS ASPIRATORS AND FLAPPER VALVE ROD.