N779LF
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
CHAFE DAMAGE WAS DISCOVERED ON THE TRANSMISSION DECK LH BEAM CAP (PN: B533K3202-201) BY A MEDICAL INTERIOR PANEL SCREW. AN APPROVED REPAIR PROCEDURE WAS COMPLIED WITH PER AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-BK117-53-2024-3189, ISSUE A DATED 16 OCT 2024, WHICH CONTAINS A DETAILED DESCRIPTION OF THE DAMAGE AND REPAIR INSTRUCTION.
CHAFE DAMAGE WAS DISCOVERED ON THE COCKPIT FLOOR (PN: B531M8002101) WHERE THE SLANT CONSOLE MEETS THE COCKPIT FLOOR. AN APPROVED REPAIR PROCEDURE WAS COMPLIED WITH PER AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-BK117-53-2024-3227, ISSUE A DATED 17 OCT 2024, WHICH CONTAINS A DETAILED DESCRIPTION OF THE DAMAGE AND REPAIR INSTRUCTION.
DENT DAMAGE WAS DISCOVERED ON THE RH ENGINE DECK PANEL (PN: B533K3339-213) THROUGH TO THE RH ENGINE MOUNT INBOARD SUPPORT BEAM (PN: B533K3316-207). AN APPROVED REPAIR PROCEDURE WAS COMPLIED WITH PER AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-BK117-53-2024-3426, ISSUE A DATED 01 NOV 2024, WHICH CONTAINS A DETAILED DESCRIPTION OF THE DAMAGE AND REPAIR INSTRUCTION.
SHORTLY AFTER TAKEOFF STARTED TO SMELL FUMES IN THE CABIN.
DURING A SCHEDULED MAINTENANCE EVENT, A CRACK WAS DISCOVERED ON TOP OF THE TAIL BOOM. THIS AIRCRAFT REMAINS OOS AT THE TIME OF THIS SUBMISSION AWAITING THE APPROVED REPAIR.
WHILE REMOVING THE VIBRATION DAMPER UNDER PILOTS SEAT FOUND STIFFENER ASSEMBLY CORRODED THAT THE VIBRATION DAMPER ATTACHES TO.
DURING ZONE INSPECTIONS, PULLED OFF THE VENT LINE GOING FROM RIGHT SIDE OF THE NR 1 ENGINE TO THE ENGINE DECK. FOUND THAT THE DRAIN COLLECTOR WAS CLOGGED WITH DEBRIS ON THE RIGHT SIDE OF THE Y-FITTING.
AFTER REMOVAL OF BLADE FITTINGS FOR NDT, CRACK DETECTED IN GRIP AREA. T
AFTER REMOVAL OF BLADE FITTINGS FOR NDT, CRACK DETECTED IN GRIP AREA.
AFTER REMOVAL OF BLADE FITTINGS FOR NDT, CRACK DETECTED IN GRIP AREA.
GENERATOR DISCONNECT LIGHT CAME ON FOR THE NR 1 GENERATOR. LANDED WITHOUT INCIDENT UNDER POWER FROM BOTH ENGINES. SWAPED STARTER/GENERATOR FROM SIDE TO SIDE. FOUND ISSUED FOLLOWED GENERATOR.
20 MINUTES INTO FLIGHT, THE NR 2 ENGINE CHIP LIGHT ILLUMINATED. ACTIVATED THE FUZZ BURNER FOR APPROX 1 SECOND AND THE LIGHT EXTINGUISHED. APPROX 1 SECOND LATER THE CHIP LIGHT ILLUMINATED AGAIN. ACTIVATED THE FUZZ BURNER AGAIN AND LIGHT EXTINGUISHED. APPROX 1 SECOND LATER THE LIGHT ILLUMINATED AGAIN. DIVERT AND MONITORED ENGINE TEMPERATURE AND PRESSURE WHICH REMAINED NORMAL. KEPT BOTH ENGINES AT FLY AND LANDED WITHOUT INCIDENT UNDER POWER FROM BOTH ENGINES. MECHANIC INSPECTED CHIP PLUG IAW MM FOUND CHIP TO BE LEVEL A. TOOK OIL SAMPLE, CHANGED OIL FILTER, AND REINSPECTING OIL FILTER IN THE NEXT 25 FLIGHT HOURS.
UPON SEVERAL ATTEMPTS TO BALANCE THE TAIL BLADE ASSY, THE MECHANIC HAD NUMEROUS CHIP LIGHT EVENTS. THE LAST INSPECTION OF THE CHIP PLUG FOUND NUMEROUS FLAKES TO DEEM THE TAIL ROTOR GEARBOX AS UNAIRWORTHY. TAIL ROTOR GEARBOX WAS REPLACED AND THE ACFT WAS RETURNED TO SERVICE.
TRANSMISSION CHIP LIGHT ILLUMINATED IN FLIGHT, THIS WAS THE 4TH CHIP LIGHT EVENT WITHIN THE PREVIOUS SEVERAL MONTHS. PREVIOUS CHIP EVENTS WERE FUZZ REQUIRING NO FURTHER ACTION, CHIP EVENT ON 6/07/11 REQUIRED TRANSMISSION CHANGE IAW AMM 63-41-00 6-2. TRANSMISSION CHANGE IN PROGRESS.
DURING THE PILOTS PRE FLIGHT, FOUND THAT THE TRIMMING SURFACE ON THE YELLOW BLADE WAS MISSING. UPON INSPECTION FOUND THE TWO RIVET HOLES, WHERE THE RIVETS HELP HOLD THE TRIMMING SURFACE TO THE BLADE, WAS IN ALMOST PERFECT CONDITION. SENT MAIN ROTOR BLADE TO AMERICAN EUROCOPTER FOR REPIAR.
FIRE EXT WARNING LIGHT ILLUMINATED ON CAD DISPLAY. AFTER INSP OF A/C FOUND, CHAFED WIRES. THE WIRE'S WERE LOCATED JUST AFT OF THE CO-PILOT'S SEAT. IN THE CABIN OVERHEAD, JUST INSIDE OF CABIN DOOR AREA. THEY WERE CHAFING AGAINST AN AIR CONDITIONING LINE. THE WIRE'S WERE REPAIR AS REQUIRED, AN TY-WRAP IN SUCH A WAY THE CHAFING AGAINST THE A/C LINES WOULD NOT HAPPEN AGAIN. GROUND FUNCTIONAL CHECKS AS WELL AS A, A/C GROUND RUN CHECK OF THE AFFECTED SYS WAS DONE. NO DEFECT'S WERE NOTED AT THAT TIME.
ENROUTE, CREW NOTICED A STRONG ELECTRICAL BURNING ODOR. A FEW MOMENTS LATER, COULD SMELL THE FUMES. ASKED IF THERE WAS ANY SMOKE OR FIRE. NONE DETECTED. DIVERTED, OPENED PILOT SIDE SLIDING WINDOW FOR FRESH AIR AND WITHIN 10 SECONDS, A STRONG ODOR OF JET FUEL ENTERED CABIN. HEADED FOR AN OPEN PARKING LOT AND LANDED WITHOUT FURTHER INCIDENT. CREW EXITED UPON LANDING TO SECURE THE AREA AROUND ACFT AND COMPLETED NORMAL ENGINE SHUTDOWNS. ACFT INSPECTED BY MECHANIC, FOUND NO OBVIOUS FUEL LEAKAGE OR ELECTRICAL FAILURES. ACFT GROUND RUN, AND OPS CHECK FLIGHT PERFORMED. NO DUPLICATION OF PREVIOUS PROBLEMS NOTED.
UPON FINAL APPROACH INTO LANDING, CREW NOTICED ONE OF THE LANDING LIGHTS WOBBLEING UNDERNEATH THE ACFT. UPON SHUTDOWN, RT REAR LANDING LIGHT HAD BROKEN FREE FROM ITS MOUNT AND WAS HANGING BY A SINGLE WIRE. MECHANIC CALLED IN TO REPAIR. VISUAL INSP REVEALED RT AFT CROSSTUBE LIGHT ASSY CRACKED. R & R WITH SERVICEABLE UNIT.
NR 2 ENGINE TORQUE SYS FAILURE.
DURING PREFLIGHT FOUND FUEL DRIPPING FROM DRAIN LINE LOCATED ON LOWER LEFT BELLY OF FUSELAGE, DRAIN LINE COVERED AND DRENCHED WITH JET FUEL, AREA FWD OF DRAIN LINE AROUND CROSS TUBE WET ALSO. FWD EDGE OF SX5 HAS A WET RESIDUE ON IT. FIBERGLASS COVER FOR REMOTE COMPASS SENSOR ON BOTTOM OF TAIL BOOM ALSO HAS A WET RESIDUE STRIKING IT AND RUNNING BACK. AIRCRAFT HAD JUST RETURNED FROM A .9 FLIGHT, FUEL DRENCHED LINE AND RESIDUE ON BOTTOM OF TAIL BOOM APPEARED AFTER A .9 FLIGHT (HOME LEG). FUEL CONTROL DID NOT PASS LEAK CHECK BY MECHANIC. ORDERED FUEL CONTROL.
SMELL OF JET FUEL EMITTED FROM HEATER AFTER TAKEOFF. IMMEDIATELY RETURNED TO PLACE OF TAKEOFF. SMELL SEEMED TO GO AWAY AFTER HEATER TURNED OFF. PILOT NOTIFIED MECHANIC OF THE FUEL SMELL IN THE COCKPIT. MECHANIC REMOVED THE DRAIN PLUG FROM THE FUEL INLET LINE TO MOD 3. PILOT GROUND RUNS THE HELICOPTER TO SEE IF FUEL WAS DRAINING FROM THE PLUG. THERE WAS NONE. MECHANIC REINSTALLED THE PLUG IAW TEC SPECS AND REPLACED THE START DRAIN VALVE. THE FUEL SMELL WAS STILL PRESENT DURING RUN UP PROCEDURES. REMOVED THE P2 AIRLINE FROM THE FCU. VERIFIED NO FUEL EXISTED IN THE P2 CHAMBER. THERE WAS EVIDENCE OF FUEL IN THE P2 PORT. DETERMINED THE FCU WAS INDEED SERVICEABLE. MECHANIC REPLACED THE 2 O-RINGS AT THE MOD 3 FUEL INLET, FLUSHED BLEED AIR LINES. GROUND RUNS AND A MOC WERE PERFORMED. THE SMELL OF BURNED FUEL VAPORS WERE GONE.
LEAD ACID BATTERY WOULD NOT HOLD CHARGE. UNIT SCRAPPED ON SITE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.
ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT FROM ONE EACH KIT P/N 355A33. (X)
ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.
LAMINATED HINGE ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS FROM KIT 350A33-2153-00, CORRECTED PROBLEM.
LAMINATED BEARING ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 4 EACH NEW UNITS FROM KIT 355A09-1036-01, CORRECTED PROBLEM.
LAMINATED HINGE ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS FROM KIT 350A33-2153-00, CORRECTED PROBLEM.
LAMINATED HINGE ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS FROM KIT 350A33-2153-00, CORRECTED PROBLEM.
HINGE ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS, FROM KIT 350A33-2153-00 CORRECTED PROBLEM.
HINGE ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED 2 EACH NEW UNITS FROM KIT 350A33-2153-00, CORRECTED PROBLEM.
TAIL ROTOR ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS FROM KIT 350A33-2153-00, CORRECTED PROBLEM.
LAMINATED HINGE HAS ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM.
ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.
SPHERICAL STOP ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.
SPHERICAL STOP ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM.
LAMINATED HINGE ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS FROM KIT 350A33-2153-00, CORRECTED PROBLEM.