N768AL
Registered owner: SIKORSKY AIRCRAFT CORP, CT (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.
12 reports on file, 1995-12-06 – 2002-07-31.
Part: WIRE — FAILED (FLOAT BOTTLE)
DURING PRESTART CHECKLIST. WHEN THE (AUX ESS POWER) CHECK WAS DONE, THE PILOT FLOAT BOTTLE DISCHARGED, AFTER APPROXIMATELY 2-3 SECONDS. WHILE SWITCH WAS ENGAGED FLOAT (ARM) SWITCH WAS OFF FLOAT (TEST) SWITCH WAS IN (NORMAL). REPAIRED CHAFFED AND BROKEN WIRE JUST FORWARD OF CONNECTOR P216 IN RIGHT FORWARD INSTRUMENT CONSOLE. RELAY K-19 (PN MS 27400-1) IN NR 2 RELAY PANEL WAS REPLACED.
Part: COMPRESSOR WHEEL — CORRODED (ENGINE)
RECEIVED TURBINE FROM FIELD TO REPAIR FOR HIGH FREQUENCY AND VIBES. REMOVED OUTER COMBUSTION CASE FROM TURBINE TO INSPECT FOR HIGH FREQUENCY AND FOUND 1ST STAGE WHEEL BLADES TO HAVE BEEN ATTACKED BY SULPHADATION. MFG SHOULD USE THE NEW GENERATION OF COATING TO STOP THIS PROBLEM.
Part: FLAME DETECTOR — FAILED (NR 1 ENGINE)
NR 1 ENGINE T-HANDLE FIRE LIGHT ILLUMINATED INTERMITTENTLY. REMOVED AND REPLACED NR 1 ENGINE FORWARD FLAME DETECTOR.
Part: WHEEL BLADES — ERODED (FIRST STAGE)
TURBINE ASSEMBLY RECEIVED DUE TO 2,000 HOUR OVERHAUL. FOUND FIRST STAGE WHEEL HAD BURNED AND ERODED BLADES CAUSED BY SULFIDATION.
Part: WHEEL BLADES — BROKEN (GP SECT 1ST STG)
TURBINE ASSEMBLY WAS RECEIVED WITH ENGINE ASSEMBLY DUE TO MAKING METAL. UPON INSPECTION OF G.P. SECTION, FOUND SULFIDATION ON 1ST STAGE WHEEL. 1ST STAGE WHEEL: PN 23053299, SN X-138702, TT 1,348.1 HOURS, TC 1,697. SCRAPPED DUE TO MISSING BROKEN AND CRACKED BLADES CAUSED BY SULFURDATION.
Part: SKIN — CRACKED (TAIL PYLON)
DURING PHASE INSPECTION, FOUND CRACK IN PYLON SKIN ACROSS RIVET HOLE. THIS CRACK EMANATED FROM CORROSION OF THE SKIN. FURTHER INSPECTION REVEALED CORROSION ON VARIOUS MEMBERS IN THE PYLON.
Part: BLADE — DEBONDED (M/R)
DURING DAILY INSPECTION, FOUND UPPER SURFACE SKIN DEBONDED APPROXIMATELY 20 INCHES BY 8.50 INCHES NEAR BLADE TIP.
Part: BLADE — CRACKED (M/R)
DURING 500-HOUR INSPECTION, FOUND BLADE SPAR CRACKED AT ROOT END BUSHING HOLE. SUBMITTER STATED CAUSE UNKNOWN.
Part: BEARING — GALLED (GEARBOX)
UPON DISASSEMBLY OF GEARBOX, CLEANED AND INSPECTED PARTS AS REQUIRED. FOUND EXCESSIVE GALLING ON PTO AFT, BEARING INNER RACE. EXCESSIVE GALLING, BEARING INNER RACE, POSSIBLY DUE TO BEARING CAGE OUT-OF-ROUND CAUSING TIGHT FIT BETWEEN INNER AND OUTER RACE AND BALLS.
Part: DETECTOR — MALFUNCTION (NR 1 ENGINE)
DURING LEVEL FLIGHT, NR 1 ENGINE FIRE T-HANDLE ILLUMINATED. PERFORMED TIGHT TURN, LOOKING FOR INDICATION OF SMOKE. NOTED NO SMOKE, ALL ENGINE INDICATIONS WERE NORMAL. DURING TROUBLESHOOTING, FOUND ENGINE NR 1 FLAME DETECTOR BAD. REPLACED FLAME DETECTOR. OPS CHECKED GOOD.
Part: WIRE — CHAFED (DL SW BOX)
DURING FLIGHT, A ELECTRICAL SPARK WAS SEEN IN THE VICINITY OF THE OVERHEAD CIRCUIT BREAKER PANEL. REMOVED OVERHEAD ON PILOT'S SIDE AND FOUND A WIRE CHAFED AGAINST THE AFT RIGHT CORNER OF THE DL SWITCH BOX. CHAFE WAS REPAIRED.
Part: BLADE ASSY — DEBOND (BLADE)
TAIL ROTOR BLADE DISBOND DETECTED DURING DAILY INSPECTION. FOUND APPROXIMATELY 1 INCH BY 1 INCH SKIN DELAMINATION AT TIP WEIGHT AREA. POSSIBLY CAUSED BY RUST FORMING ON TIP WEIGHT HARDWARE.