N242CH
Registered owner: COLUMBIA HELICOPTERS INC, OR (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| COLUMBIA HELICOPTERS, INC (CHIA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
DURING FLIGHT PIC/SIC NOTICED SLIGHT BURNING SMELL IN COCKPIT IN FWD FLIGHT AFTER DEPARTING DIP SITE. PIC IMMEDIATELY TURNED OFF THE HEAT VENT MASTER SWITCH, AFTER WHICH NO FURTHER SMELLS WERE NOTED. CONTINUED MISSION FOR APPROXIMATELY 15-20 MINUTES AND THEN RETURNED TO BASE. AFTER LANDING, DISCOVERED POPPED CIRCUIT BREAKER ON THE NO. 1 PDP. RESET CIRCUIT BREAKER AND IT REPEATEDLY POPPED. REMOVED CANON PLUG TO HEATER BLOWER AND RESET CIRCUIT BREAKER. TURNED ON HEATER BLOWER AND THE CIRCUIT BREAKER DID NOT POP. R&R HEATER BLOWER, OPS CHECKED GOOD.
DURING FLIGHT PIC/SIC NOTICED SLIGHT BURNING SMELL IN COCKPIT IN FWD FLIGHT AFTER DEPARTING DIP SITE. PIC IMMEDIATELY TURNED OFF THE HEAT VENT MASTER SWITCH, AFTER WHICH NO FURTHER SMELLS WERE NOTED. CONTINUED MISSION FOR APPROXIMATELY 15-20 MINUTES AND THEN RETURNED TO BASE. AFTER LANDING, DISCOVERED POPPED CIRCUIT BREAKER ON THE NO. 1 PDP. RESET CIRCUIT BREAKER AND IT REPEATEDLY POPPED. REMOVED CANON PLUG TO HEATER BLOWER AND RESET CIRCUIT BREAKER. TURNED ON HEATER BLOWER AND THE CIRCUIT BREAKER DID NOT POP. R&R HEATER BLOWER, OPS CHECKED GOOD.
WE JUST COMPLETED ABOUT 2 HOURS ON A FIRE FIGHTING MISSION 15NM WEST OF BECIN FOREST SERVICE BASE AND WERE RETURNING TO BECIN BASE FOR FUEL. ABOUT HALF WAY BACK TO BASE THE XMSN HOT LIGHT ILLUMINATED ON THE ANNUNCIATER PANEL. WE PULLED OUT THE CHECK LIST AND LOOKED FOR SECONDARY INDICATIONS, XMSN PRESSURES WERE ALL NORMAL BUT THE XMSN TEMP ON THE RIGHT SIDE ENGINE XMSN NOSE BOX WAS BEYOND THE REDLINE APPROXIMATELY 150C. PER THE EMERGENCY CHECKLIST WE SHUT DOWN THE NUMBER TWO ENGINE, BEEPED UP THE NUMBER ONE ENGINE TO MAINTAIN 100% RPM AND PROCEEDED TO THE NEAREST SAFE LANDING AREA WHICH WAS MILAS-BODRUM AIRPORT. AN EMERGENCY WAS DECLARED FOR PRIORITY. OUR WEIGHT, LANDING ELEVATION, AND STRONG WINDS OUT OF THE NW WERE ALL CONSIDERED. OUR PERFORMANCE ALLOWED US TO LAND ON ONE ENGINE FROM AN OGE HOVER WITH LINE ATTACHED.
DURING REMOVAL OF THE AFT EMERGENCY EXIT HATCH, FOUND CRACK AT STA 482, BL 50L, WL +50. REMOVED DAMAGED WEB, LOCATED AND INSTALLED NEW WEB P/N 145S3106-5 (PO# A043423) IAW 234-3 SRM REV. 2, SECTIONS 53-13-03 AND 51-50-00.
THE MAINTENANCE CREW REMOVED THE AFT TRANSMISSION DUE TO AN OIL LEAK AND DISCOVERED A CRACKED FWD R/H MOUNT LUG. COMPONENT RECEIVED AT THIS REPAIR STATION 6/7/2019 AND CONFIRMED CRACKED UPPER HOUSING. THE TRANSMISSION WAS THEN INSPECTED AND REPAIRED BY THIS RS ON SWO-047697-19. DETAILS ARE ON FILE.
DURING RAMP CHECK, NOTICED OIL LEAK ON TOP OF AFT XMSN. SUSPECTED AFT VERTICAL SHAFT OIL SEAL. UPON REMOVAL AND FURTHER INSPECTION OF THE AFT XMSN, FOUND FWD RT MOUNT LUG CRACKED. FOUND 1 CRACK BY VISUAL INSPECTION AND CONFIRMED BY STRIPPING PAINT ON UPPER HOUSING. CRACK MEASURES APPROX. 5" EXTENDING FROM THE TOP OF THE SLING ATTACHMENT LUG, EXTENDING TO THE LOWER UPPER HOUSING.
FOUND CRACK IN AFT TRANSMISSION AREA DURING "A" CHECK, STA. 575, WL +36, BL 35R. REMOVED EXISTING 2 DOUBLERS, CUT OUT CRACKED AREA AND FABRICATED FILLER. FABRICATED REPLACEMENT DOUBLER, AND LOCATED AND INSTALLED FILLER DOUBLER AND REPAIR DOUBLER. ALL WORK DONE IAW 234-3 SRM. 337 FILED.
ON DEPARTURE THE XMSN CHIP LIGHT ILLUMINATED. THE AIRCRAFT RETURNED TO THE LANDING FOR FURTHER INSPECTION, WITH NO FURTHER ISSUES. THE AFT TRANSMISSION CHIP DETECTOR WAS INSPECTED, AND CHIPS WERE NOTED. THE TRANSMISSION WAS REMOVED AND REPLACED.
NR 1 ENGINE FIRE WARNING IN-FLIGHT AT END OF DAYS OPERATIONS AT HOVER. MECHANIC CONFIRMED FIRE AFTER ACFT WAS SET DOWN. FIRE AT 12:00 ON TOP AND BACK OF BURNER CAN. AFTER ENGINE WAS SHUTDOWN, THE FIRE WENT OUT. ENGINE WAS INSPECTED. NO EVIDENCE OF CRACKING FOUND BUT SOOT WAS EVIDENT AT THE 12 O'CLOCK POSITION ON FUEL MANIFOLD. PRIOR TO START UP, IN TEST CELL, FUEL WAS OBSERVED LEAKING FROM THE FUEL MANIFOLD COVER PLATES, IPC, REV 3, FIG 9, SHEET 6, ITEMS 131, 132, AND 133. START ATTEMPT ABORTED FOR FIRE CONCERNS. REMOVAL OF FUEL MANIFOLD COVER PLATES ITEMS 131 AND 133 REVEALED HARDENED AND CRACK PACKING, ITEM 132. REPLACED PACKING AND PERFORMED ENGINE TEST. NO FURTHER LEAKS.
DURING DISASSEMBLY OF COMPONENT, SCUFFING ON BOTH THE SPIRAL BEVEL GEAR AND PINION GEAR WAS NOTED. THE CUSTOMER HAD REPORTED A SINGLE BOLT BROKEN UPON ON-WING TORQUE CHECK INSPECTION AND NO OTHER BOLTS APPEAR CRACKED AFTER DISASSEMBLY. NDT PENDING RESULTS. THIS BOLTED JOINT HAS HAD THE UPDATED TORQUE VALUE APPLIED AT LAST SHOP REPAIR.
A POST REPAIR FLOURESCENT PENETRANT INSPECTION WAS PERFORMED ON A PITCH HOUSING AFTER SOME MINOR BLENDING TO REMOVE PITTING. AN INDICATION OF A CRACK WAS DISCOVERED ON THE OTBD RADIUS OF THE TT PIN BORE.
CASE ASSEMBLY AT WEB OR LINER 247 HAS INDICATION OF A CRACK APPROXIMATELY 1.5" LONG. CRACK AT HOUSING IN PREVIOUS WELD REPAIR LOCATED NEAR ROTOR BRAKE HOUSING SUPPORT BORE. CRACK IS LOCATED ON OUTSIDE OF HOUSING.
ENGINE TRANSMISSION SPIRAL BEVEL GEAR WAS FOUND TO BE CRACKED ACROSS GEAR TOOTH, .2500" FROM THE HEEL.
THE CONNECTING BOLT WAS REMOVED FROM THE ROTOR HEAD AND A HAIR LINE CRACK WAS FOUND UNDER THE HEAD OF THE BOLT DURING A VISUAL INSPECTION. THE CRACK WAS CONFIRMED BY AN NDT INSPECTION.
DURING OVERHAUL OF ENGINE AWN ADAPTER, NDT FOUND .450 INCH TOTAL LENGTH CRACK IN THE BOLT HOLE OF LUG NR 1. IN THE BORE OF LUG, CRACK LENGTH IS .300 OF INCH AND ACROSS FACE OF LUG, THE CRACK LENGTH IS .150 OF INCH. ILLUSTRATION DEPICTS LOCATION AND SCHEMATIC OF CRACK FOUND. FIRST TIME CRACK OF THIS NATURE NOTED ON THIS ADAPTER. CHECKED OTHER ADAPTERS MFG UNDER THIS LOT NR. THIS REVIEW CONCLUDED THAT THE CRACKED ADAPTER IS AN ISOLATED INCIDENT AND NOT RELATED TO MATERIAL DEFICIENCIES. (K)
TWO CRACKS WERE FOUND IN THE 1ST STAGE COMPRESSOR DISC (PN210133105) DURNG AN INSPECTION. THE CRACKS ARE LOCATED IN TWO OF THE COMPRESSOR BLADE RETENTION SLOTS. THIS IS THE SECOND TIME CRACKS HAVE BEEN FOUND EMANATING FROM THE BLADE RETENTION SLOTS OF THIS PN DISC. AFTER THE FIRST OCCURRENCE, THE MANUFACTURER CHANGED MANFACTURING PROCESSES AND REIDENTIFIED THE COMPRESSOR DISC. NO CRACKS HAVE BEEN DETECTED IN THE IMPROVED DISCS. WILL CONDUCT A ONE TIME DETAILED INSP OF ALL OLD STYLE COMPRESSOR DISCS. CONSIDERATION WILL BE GIVEN TO ACCELERATING THE REPLACEMENT OF ALL 1ST STG COMP DISC WITH THE IMPROVED DISC.(K)