N382AM
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
A CRACK WAS DISCOVERED ON THE TOP FLANGE OF THE RH EDGE FRAME "Z" CHANNEL JUST AFT OF THE STA 845 FRAME. THE CRACK IS APPROXIMATELY 0.75" LONG.
ELECTRICAL SMOKE ODOR IN CABIN. AFT EVAPORATOR MOTOR HAD INTERNAL SHORT CAUSING SMOKE SMELL AND CAUSING AFT PORTION OF A/C TO BE INOP.
N382AM 7029 WENT OOS FOR SCHEDULED HEAVY MAINTENANCE, WHILE REMOVING THE HORIZONTAL STABILIZER TO FOM, IT WAS NOTED THAT THE RH ATTACHMENT BOLT WAS VERY HARD TO REMOVE. UPON FURTHER INSPECTION, FOUND THE HORIZONTAL RH UPPER ATTACHMENT FITTING TO BE CRACKED.
UPON DEPARTURE FROM THE AIRFIELD AT 0133, AT 500' AGL, 70 KIAS, AND 8.5 FLI WITH THE DEMIST ON, SMOKE BEGAN FILLING THE COCKPIT ORIGINATING FROM THE DEMIST NOZZLES. CREW OPENED THE SLIDING WINDOWS TO VENT THE COCKPIT, DEMIST WAS SHUT OFF, AND THE AIRCRAFT WAS RETURNED TO BASE WITHOUT FURTHER INCIDENT. WHEN THE AIRCRAFT WAS ON THE GROUND AT "FLY" DEMIST WAS TURNED BACK ON AND LIGHT SMOKE BEGAN COMING OUT OF THE NOZZLES. DEMIST WAS SHUT OFF AND THE AIRCRAFT WAS SHUT DOWN.
DURING PAINT STRIPPING, MAJOR CORROSION WAS FOUND ON THE RT CABIN THRESHOLD RAIL FROM FS 1436.0 MM TO FS 2230.0 MM.
WHILE ON A FLIGHT, STARTED EXPERIENCING INCREASE LIGHT NOISE IN THE FRONT AND RIGHT PORTION OF THE CABIN TO THE POINT WHERE IT STARTED TO LIMIT OUR NVGS CAPABILITIES. MENTIONED TO THE CREW THERE WAS A LIGHT FLICKERING TOWARDS THE FRONT OF THE CABIN AND IF ANY OF THE CREWMEMBERS COULD INVESTIGATE. INITIALLY THOUGHT IT WAS A LIGHT COMING FROM THE ZOLL MONITOR THAT WAS SHINING TOWARDS THE FRONT JUST TO FIND OUT THAT WAS NOT IT. CONTINUE TO INVESTIGATE THE CAUSE AND DETERMINED THAT THE LIGHT WAS COMING FROM THE RT SUPER NIGHT SCANNER SEARCHLIGHT, BY TURNING THE SEARCHLIGHT ON AND OFF AND WATCHING THE FLICKERING LIGHT DISAPPEAR AND APPEAR AGAIN. ON THE GROUND AND AFTER SHUT DOWN, LOOKED OVER THE AREA OF CONCERN, DISCOVERED THAT THE BOTTOM OF THE RT WINDSCREEN PROSEAL HAD CRACKED AND THE WINDSCREEN WAS DIS-BONDING FROM THE AIRFRAME LEAVING A SIZEABLE GAP WHERE LIGHT WAS COMING INTO THE CABIN. IMMEDIATELY NOTIFIED MAINTENANCE. MAINTENANCE DECIDED THAT THE AIRCRAFT WILL HAVE TO REMAIN OVERNIGHT AT THE LANDING AREA AND THEY WILL TAKE CARE OF THE ISSUE IN THE MORNING
AFTER DEPARTURE, CREW NOTICED A TEN INCHES CRACK IN THE RIGHT WINDOW. THIS CRACK WAS NOT NOTICED DURING PREFLIGHT. FLIGHT WAS IMMEDIATELY TERMINATED AND RETURNED TO BASE. FURTHER INSPECTION BY PILOT REVEALED NO OBVIOUS DAMAGE RESULTING IN THE CRACK NOR INDICATIONS OF BIRD STRIKE . PREVIOUS FLIGHT DURING THE DAY (1216-00282) CREW CLAIMED THAT THE CRACK WAS NOT THERE DURING OR AFTER THE FLIGHT. THE CRACK WAS NOT NOTICED DURING PREFLIGHT DURING NIGHT SHIFT. AFTER DEPARTURE THE CRACK WAS NOT NOTICEABLE UNDER NVG'S. THE RIGHT SIDE CREW MEMBER ONLY NOTICED THE CRACK AFTER LOOKING UNDERNEATH THE NVG'S, WHILE SCANNING. MAINTENANCE WAS NOTIFIED.
PILOTE SMELLED AN ELECTRICAL BURNING ODOR IN THE COCKPIT. NO VISABLE SMOKE. THE ODOR SEEMED TO ORIGINATE WHEN TRANSMITTING ON THE MEDICAL RADIO INSTALLED IN THE AIRCRAFT. MECHANIC STATED THERE WAS NO EVIDENCE OF A BURNING ODOR IN THE COCKPIT. MECHANIC TRANSMITTED ON THE RADIO, A STRONG BURNING ODOR WAS NOTICED. TURNED OFF ALL ELECTRICAL POWER IMMEDIATELY AND SEARCHED FOR THE ORIGIN OF THE ODOR. FOUND THAT THE ANTENNA FOR THE RADIO, WHICH IS LOCATED ON THE FORWARD CENTER BELLY PANEL, HAD BURN MARKS AROUND THE BASE WHERE IT ATTACHED TO THE PANEL. THE CAUSE OF THE ODOR HAS BEEN DETERMINED TO BE A SHORT IN THE ANTENNA, WHICH WAS ACTUALLY BURNING THE BELLY PANEL. THE PANEL IS BEING SCHEDULED TO BE REPAIRED.
WHILE DIAGNOSING WIRING ISSUE, LEFT FRONT BELLY PANEL WAS REMOVED & A CANOPY WEB CRACK WAS DISCOVERED.
DURING A0560 100 HR 12 MONTH AIRFRAME INSPECTION, TWO CRACKS WERE DISCOVERED. ONE ON LT SIDE OF ACFT BETWEEN SLIDING DOOR & BAGGAGE DOOR, EXTENDING 115MM DOWN THE SIDE OF THE AIRCRAFT & UPWARD TO FRONT OF THE DOOR TRACK. THE OTHER CRACK IS ON THE RT SIDE OF ACFT IN EXACTLY THE SAME SPOT AS THE LT SIDE, BUT ONLY EXTENDING DOWN THE SIDE OF THE AIRCRAFT 25MM, BUT EXTENDING UPWARD INTO THE STIFFENER WALL BETWEEN THE CANOPY & MGB DECK.
DURING AAIP A1040 300 HOUR, 12 MONTH INSPECTION, STEP A1040 2.4, A CRACK WAS FOUND IN THE LT UPPER STABILIZER MOUNT DURING THE VISUAL INSPECTION. THE CRACK RAN FROM THE FWD EDGE OF THE MOUNT THROUGH THE FWD OTBD BOLT HOLE & TO THE MIDLINE OF THE MOUNT.
DURING A 100 HOUR INSPECTION, A CRACK WAS FOUND IN THE SKIN ADJACENT OF THE RT CANOPY WEB. THE SKIN CRACK HAS APPROXIMATELY 30MM VISIBLE LENGTH PARALLEL TO INBD EDGE OF THE RT CANOPY WEB. IT TURNS OTBD ALONG THE TOP RADIUS OF THE CANOPY WEB. IT IS POSSIBLE THERE IS MORE LENGTH BENEATH THIS WEB. THE CRACK IS APPROXIMATELY LOCATED AT STA X845 AND BUTT LINE Y1000.
DURING A ROUTINE AIRWORTHINESS CHECK, MECHANIC PERFORMED A VISUAL INSPECTION OF THE ACFT. ON INSPECTING THE HORIZONTAL STABILIZER AREA, A CRACK WAS NOTICED ON THE RT LOWER CARRIER ATTACH FITTING. REPLACED CRACKED CARRIER.