N145SJ
Registered owner: AIR METHODS LLC, CO (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| AIR METHODS LLC (QMLA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
DURING 800-HOUR INSPECTION, FOUND DAMAGE TO THE COCKPIT FLOOR (P/N: B531M8002101) IN THE FORM OF DENTS TO THE UPPER SKIN PANEL BETWEEN THE PILOT SEAT TRACK NEAR THE AFT SIDE OF THE CYCLIC OPENING. THE INBD DENT DAMAGE MEASURED TO BE APPROXIMATELY 1.90â IN DIAMETER AND 0.15â IN DEPTH. THE OTBD DENT DAMAGE MEASURED TO BE APPROXIMATELY 2.0â IN DIAMETER AND 0.187â IN DEPTH. A DETAILED DESCRIPTION OF THE DAMAGE AND APPROVED REPAIR PROCEDURES ARE PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-BK117-53-2024-3393A ISSUE A DATED 01 NOVEMBER 2024.
DURING 800 HOUR INSPECTION, DAMAGE TO THE FORWARD BOTTOM FRAME 1 IN THE FORM OF A CRACK WAS DISCOVERED AT LBL 195MM AND IS APPROXIMATELY 1.2â IN LENGTH. A DETAILED DESCRIPTION OF THE DAMAGE AND APPROVED REPAIR PROCEDURES ARE PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-BK117-53-2024-3340.
2 CRACKS WERE FOUND IN THE TAILCONE OF AIRCRAFT DURING A 1200 HOUR INSPECTION ON A SECTION OF FRAME AT STATION 6616 AND THE ATTACHED DOUBLER. THESE CRACKS WERE REPAIRED AND DOCUMENTED ON AN FAA FORM 337 DATED 01/29/2019.
DURING AN AIRFRAME ZONE 12 INSPECTION FOUND THE SHELF THAT THE ANTI-COLLISION LIGHT POWER SOURCE IS MOUNTED TO IS BROKEN & UPON FURTHER INSPECTION FOUND A CRACK IN UPPER FRAME 9LA.
TAILROTOR CHIP LIGHT CAME ON IN FLIGHT SOON AFTER TAKEOFF. PILOT USED FUZZ BURNER BUT LIGHT STAYED ON. ACFT RETURNED TO AIRPORT. FOUND CHIPS CONSISTENT WITH FIGURE F IN AMM 65-21-00, 6-1.
IN FLIGHT, PILOT AND PASSENGERS DETECTED THE ODOR OF SMOKE. NO SMOKE OR EVIDENCE OF FIRE WAS VISIBLE INSIDE OR OUTSIDE THE ACFT. PILOT SHUTOFF BOTH GENERATORS AND AIR CONDITIONER IAW CHECKLIST. ACFT MADE A PRECAUTIONARY LANDING AND PERFORMED AN EMERGENCY SHUTDOWN OF BOTH ENGINES. NO EVIDENCE OF SMOKE, FIRE, OR BURNING WAS FOUND DURING POST-FLIGHT INSPECTION. MX PERSONNEL LOCATED A BROKEN AIR CONDITIONER DRIVE BELT. ACFT WAS RUN AND FLOWN WITH NO FURTHER SMOKE ODOR.
WHILE PERFORMING TU360 UPGRADE TO ENGINE SN 18789 FOUND THE SECOND STAGE TURBINE DISK BLADE LOCKS DISPLACED LEADING TO BLADE SHIFT. R & R MODULE 3.
PILOT REPORTED AFTER TAKEOFF THEY SMELLED FUEL ODOR IN CABIN. INSPECTED ENGINES AND AIRFRAME FUEL EXPANSION BOX FOR EVIDENCE OF FUEL AND LEAKS. NO LEAKS OR FUEL WERE FOUND. DURING INSP OF THE EXPANSION BOX THE OUTER DUCT AROUND THE LOWER FUEL VENT LINE WAS FOUND DISCONNECTED FROM THE STRUCTURE. OUTER DUCT LISTED BELOW HAD SLIPPED DOWN THE STRUCTURE OUT FROM UNDER THE CABLE TY THAT HOLDS IT. REINSTALLED OUTER DUCT IAW MM CHAPTER 28-22-00, 4.5. PERFORMED GROUND RUN. NO LEAKS OR FUEL ODORS WERE DETECTED. PERFORMED MX CHECK FLIGHT AND NO FUEL ODOR WAS DETECTED.
A RIVET HEAD WAS FOUND MISSING ON THE DOUBLER ON THE RT SIDE OF THE VERTICAL FIN AT THE TAILBOOM/ VERTICAL FIN TRANSITION. FURTHER INSP REVEALED A CRACK IN THE VERTICAL FIN FWD BULKHEAD/ SPAR STRUCTURE, STARTING FROM THE TOP RT AFT RECEPTACLE HOLE FOR THE TRANSITION COVER, RUNNING TO THE EDGE OF THE FLANGE. ANOTHER CRACK WAS FOUND, STARTING ON THE OTHER SIDE OF THE HOLE, RUNNING TOWARDS THE FLANGE RADIUS. DYE PENETRANT VERIFIED THE CRACKS. THE RIVET WAS REPLACED AND A REQUEST WAS SUBMITTED TO AEC FOR REPAIR INSTRUCTIONS.