N54178
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 Corp. (QMLA) | Certificate holder | — | Matched by certificate designator |
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.
9 reports on file, 2011-01-13 – 2022-05-27.
Part: BULKHEAD — CHAFED (ZONE 200) · airframe 6,893 hrs · 17,430 cycles
DAMAGE WAS NOTED TO THE 15 DEGREE BULKHEAD LH WEB (P/N: 350A21-1032.86) IN THE FORM OF CHAFES. THE TWO CHAFING DAMAGE AREAS WERE FOUND NEAR THE X-FRAME AND UPPER CHAFING DAMAGE WAS MEASURED TO BE APPROXIMATELY 0.20â IN LENGTH, 0.3â IN WIDTH AND 0.008â DEPTH; THE LOWER CHAFING DAMAGE WAS MEASURED TO BE APPROXIMATELY 0.20â IN LENGTH, 0.2â IN WIDTH AND 0.010â DEPTH
Part: DOOR FRAME — CORRODED (RT SIDE) · airframe 5,356 hrs · 13,063 cycles
RIGHT SIDE LOWER DOOR FRAME FOUND CORRODED.
Part: FRAME — CHAFED (NOT REPORTED) · airframe 5,356 hrs · 13,063 cycles
RIGHT X FRAME STRUCTURE CHAFED.
Part: BLADE — CRACKED (TAIL ROTOR) · airframe 5,161 hrs · 12,509 cycles
TAIL ROTOR BLADE CRACKED, 7 INCHES DOWN FROM COLLAR, 3 INCHES LONG . FOUND TO BE OUT OF LIMITS IAW AMM 64-10-00,6-1A.
Part: STARTER GEN — DAMAGED (ENGINE) · airframe 3,907 hrs · 9,145 cycles
WHILE ACFT WAS IN FLIGHT WITH A PATIENT ABOARD, PILOT NOTICED A GRADUAL LOSS OF VOLTAGE & AMPERAGE. AFTER SHEDDING SECONDARY ELEC EQUIP, VOLTAGE & AMPERAGE CONTINUED TO DECREASE WHILE A GEN LIGHT ILLUMINATED DURING FINAL DESCENT ON TO A MALL PARKING LOT. REMOVED STARTER GEN FOR INSPECTION & FOUND THAT THE BRUSH BRAID ATTACH POINTS WERE IN PIECES. THE BRAID ATTACH RIVETS ON THE BRUSHES BECAME LOOSE, THEN SEPARATED.
Part: TRAY — CRACKED (TAILBOOM) · airframe 3,475 hrs · 8,050 cycles
DISCOVERED CRACKS IN AFT TAIL BOOM MOUNTED BATTERY TRAY. FIRST CRACK WAS LOCATED ON RT BATTERY TRAY. THIS CRACK WAS ON THE RT NUTPLATE DOUBLER FOR THE RT BOLT HOLE THAT ACCOMMODATES THE BATTERY HOLD DOWN BRACKET. SECOND CRACK WAS LOCATED ON THE LT BATTERY TRAY AT THE AFT LT BOLT HOLE LOCATION. THIS CRACK WAS IN THE SHAPE OF A J & TOTALED A LENGTH OF 45 MM. THESE CRACKS APPEAR TO BE STRESS RELATED WHEN THE BATTERY HOLD DOWN BRACKETS ARE INSTALLED & TIGHTENED.
Part: HOSE — LEAKING (HYD SYSTEM) · airframe 3,000 hrs · 6,836 cycles
GROUND RUN HYD FLUID COMING FROM HOSE END FITTING GOING INTO HYD MAINFOLD. NEW HOSE WAS INSTALLED 1:43 HOURS AGO. REPORTED HAVING PROBLEMS WITH THIS HOSE. LOOKS LIKE POSSIBLE BAD CRIMPING OF HOSE ONTO FITTING. INSTALLED SERVICABLE HOSE OF AN OLDER PN. RUN UP NO LEAKS ON GROUND RUN.
Part: RECEPTACLE — FAILED (FDC) · airframe 2,900 hrs · 4,862 cycles
ON THE FDC AIR FILTER SYS, FOUND THE ENCAPSULATED RECEPTACLE, P26R16-1 HAD FAILED. THE CAPSULE WHICH IS HELD IN PLACE BY WHAT LOOKS LIKE "METAL SET" HAD SEPARATED FROM THE .2500 TURN FASTENER AND DROPED INTO THE ENGINE BAY. ON FURTHER INSPECTION SEVERAL OTHER CAPSULES WERE FOUND LOOSE.
Part: POTENTIOMETER — BINDING · airframe 2,027 hrs
ACFT WAS LEAVING AIRPORT, DURING FLIGHT ACFT HAD A YAW FLUCTUATION. AFTER SEVERAL YAW FLUCTUATIONS THE WARNING INDICATION PANEL DISPLAYED AN AMBER GOV LIGHT. DURING THIS TIME OF OCCURANCE THE PILOT REPOSITIONED THE ACFT TO AIRPORT AND LANDED WITHOUT INCIDENT.