N805LF
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
THE MAIN GEARBOX SUPPORT FRAME (P/N: 350A21-1041-143) HAS CHAFING DAMAGE ON THE LOWER FLANGE FROM THE TAIL ROTOR CONTROL CABLE. THE DAMAGE IS UNDER THE MAIN GEARBOX DECK AT THE AFT R/H CORNER OF THE MAIN GEARBOX CUTOUT
DAMAGE WAS DISCOVERED ON THE L/H BEAM UNDER THE ENGINE DECK (P/N: 355A21-2110.25) IN THE FORM OF AN ELONGATED HOLE IN THE LOWER FLANGE, NEAR THE AFT END OF THE PART
AC 4559 HAS CHAFE DAMAGE ON THE ENGINE DECK JUST FWD OF THE SCUPPER DRAIN OPENING LOCATED AT APPROXIMATELY STA 4370, WL 1759, AND BL 650L. THE DAMAGE IS IN AN AREA 1.4â WIDE BY .8â LONG AND MEASURES .019â AT ITS DEEPEST POINT.
WHILE PERFORMING 600HR INSPECTION THE TRANSMISSION WAS PULLED OFF THE AIRCRAFT TO PERFORM AIRBUS ASB AS350-62.00.42 REV.0 DATED 17-SEPT-2018(AIRMETHODS E) 00-6200-EO-2626)THE MAST INSPECTION WAS PERFORMED AND THE MECHANIC NOTICED CORROSION AND PITTING ON THE BEVEL HOUSING FLANGE AREA.THE AREA OF 7" WAS ALSO MISSING PRIMER. CONTACTED AIRBUS FOR ASSISTANCE AND WAS NOTIFIED THAT THE CORROSION WAS TO EXTENSIVE AND NEEDS TO HAVE A REPAIR SCHEME OR REPAIR SHOP FIX THE AREA OF DAMAGE. ORDERED A NEW BEVEL GEAR ASSEMBLY. NOTE: THIS AIRCRAFT REMAINS OUT OF SERVICE AT THE TIME OF THIS SUBMISSION AWAITING A REPLACEMENT BEVEL REDUCTION GEARBOX.
DURING AN ONGOING 600 HOUR/24 MONTH AIRFRAME INSPECTION, THE MECHANICS NOTICED ON THE REMOVAL OF THE TAIL ROTOR BLADE WHAT APPEARED TO BE A CRACK IN THE PAINT ON THE RIGHT HAND SIDE OF TAILBOOM. UPON FURTHER INSPECTION, THE CRACK EXTENDED 8 INCHES IN TOTAL. IT LOOKS LIKE IT STARTED FROM A RIVETED DZUS FASTENER RECEPTACLE FOR THE AFT TAIL ROTOR COWLING. THE CRACK STARTED TOWARDS THE VERTICAL STABILIZER MOUNTING BOLT HOLES, AND STOPPED ABOUT 1/4 INCH AWAY. ANOTHER CRACK STARTED FROM ANOTHER RIVET HOLE ON THE SAME DZUS FASTENER RECEPTACLE BUT WAS ONLY ABOUT AN INCH LONG LONG WHEN FOUND. THIS AIRCRAFT REMAINS OUT OF SERVICE AT THE TIME OF THIS SUBMISSION AWAITING AN APPROVED REPAIR PROCEDURE FROM THE MANUFACTURER.
DURING AIRWORTHINESS CHECK, FOUND MAIN ROTOR HEAD BLUE FREQUENCY ADAPTER WITH A CUT & CRACK IN THE RUBBER, AREA B, OUT OF LIMITS IAW AMM.
MAST BEARING INNER RACE HAS BECOME DEBONDED FROM THE MAIN ROTOR SHAFT. MAIN ROTOR SHAFT WAS REMOVED AND SENT FOR REPAIR. INSTALLED SERVICEABLE SHAFT TO RETURN ACFT TO SERVICE. DO NOT KNOW WHAT HAS CAUSED THE INNER RACE OF THE MAST BEARING TO DE-BOND AND SPIN ON THE MAIN ROTOR SHAFT. THIS IS THE THIRD ACFT WE HAVE INSPECTED WITH 600 TO 800 HOURS TIME IN SERVICE AND FOUND THE BEARING INNER RACE DE-BONDED.
DURING THE 1ST 600 HR INSP OF THE MAIN ROTOR HEAD AND VIBRATION ABSORBER ASSY FOUND PN 350A 31 2023 04 TO HAVE APPROX .5" CRACK IN THE RADIUS. DISASSEMBLED VIBRATION ABSORBER AND REPLACED BRACKET PN 350A 31 2023 04 WITH TSN 0.0 REASSEMBLED VIBRATION ABSORBER. INSTALLED ON ACFT AND BALANCED MAIN ROTOR HEAD. NOTE: CRACK WAS FOUND DURING MX AND VIBRATION ABSORBER WAS ALREADY REMOVED THEREFORE MINIMUM IMPACT FOR ACFT DOWN TIME. IF CRACK WOULD HAVE BEEN FOUND OUTSIDE OF MX, CONSIDERABLE DOWN TIME WOULD HAVE BEEN CREATED ON AN ACFT THAT HAD JUST OVER 600 HRS.