N4282
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 |
| OMNIFLIGHT HELICOPTERS INC | Operator | on 2010-03-16 | Operator named in NTSB report |
Accident & incident history
Operated by Omniflight Helicopters inc. (per NTSB report)
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.
8 reports on file, 2011-03-05 – 2022-01-18.
Part: SKIN — CHAFED (TAIL BOOM) · airframe 4,517 hrs · 18,056 cycles
TAILBOOM P/N 350A23-0000-0705 S/N TB4490 SKIN DAMAGE AT APPROXIMATELY X1219 RBL 228. THE DAMAGE IS MINOR CHAFING MEASURING 0.005â AT ITS DEEPEST.
Part: TAIL BOOM — CHAFED (ZONE 100) · airframe 4,517 hrs · 18,056 cycles
TAIL BOOM SERVO RH BEAM (PN: 350A23-4015.24) IN THE FORM OF A CHAFE. THE CHAFE DAMAGE WAS MEASURED TO BE APPROXIMATELY 0.50â X 0.10â AND 0.015â DEEP.
Part: NONE — DENTED (ZONE 400) · airframe 4,517 hrs · 18,056 cycles
DAMAGE TO THE ENGINE DECK (PN: 350A21-1239.21) IN THE FORM OF 3EA DENTS AND A CHAFE. THE CHAFE DAMAGE AREA WAS DISCOVERED TO BE NEAR THE SCUPPER DRAIN HOLE.
Part: FRAME — CHAFED (ZONE 100) · airframe 4,013 hrs · 15,002 cycles
L/H INBOARD SIDE OF AFT LOWER LEG OF THE X-FRAME HAS CHAFFING MEASURING APPROXIMATELY 0.011" DEEP AND 0.3" WIDE BY 2.4".
Part: SUPPORT FRAME — CHAFED (FUSELAGE) · airframe 2,993 hrs · 8,642 cycles
THE TRANSMISSION SUPPORT FRAME, PN 350A21-1041-143, HAS CHAFING DAMAGE ON THE LOWER FLANGE FROM AN UNSECURED CABLE, PN 704A34-1302-23. PN 350A38-1040-20 ATTACHES TO PN 350A21-1041-143.
Part: BLADE — DAMAGED (TAIL ROTOR) · airframe 1,470 hrs
UPON APPROACH, ACFT SUSTAINED A BIRD STRIKE ON THE PILOT SIDE WIND SCREEN AND WAS PROJECTED INTO THE TAIL ROTOR DUE TO THE DOWN WASH OF THE MAIN ROTOR SYS TECH INSPECTED WINDSCREEN WITH NO DEFECTS NOTED. TAIL ROTOR BLADE AND SPIDER ASSY HAD EVIDENCE OF THE BIRD IMPACT AND WAS INSPECTED, CLEANED, AND TAP TESTED WITH NO DEFECTS NOTED. AFTER GROUND RUNS AND OPS CHECK FLIGHT THERE WERE NO DEFECTS NOTED AND ACFT WAS RETURNED TO SERVICE. ALL WORK WAS PERFORMED IAW MET 05.53.00.604.
Part: DISPLAY — MALFUNCTIONED (CTR FWD PANEL) · airframe 1,460 hrs
DURING APPROACH TO AIRPORT, ACFT INDICATED AN AMBER GOV LIGHT. DOWNLOADED VEMD FAIL 1 CODE OF 0008 AND A FAIL 2 CODE OF 0200. AFTER CONTACTING MFG REPRESENTATIVE IT WAS VERIFIED THAT THESE DISTURBANCES ARE KNOWN AS NUISANCE CODES. CONNECTOR PLUGS WERE CLEANED BEHIND VEMD, BATTERY WAS RESET AND CODES DISTINGUISHED. AFTER SEVERAL POWER CYCLES, CODES DID NOT APPEAR AND ACFT WAS RETURNED TO SERVICE WITH NO FURTHER DEFECTS NOTED. ALL WORK WAS PERFORMED IAW CUURENT SPM 20.04.01 AND MET 31.60.00.
Part: POTENTIOMETER — MALFUNCTIONED (COLLECTIVE) · airframe 1,360 hrs
ACFT INDICATED AN AMBER GOV LIGHT IN FLIGHT, WITH NO ENGINE, MAIN ROTOR, OR TAIL ROTOR FLUCTUATIONS IN FLIGHT. TECH RETRIEVED AN INTERMITTENT FAILURE CODE 122 FOR THE COLLECTIVE POTENTIOMETER. WHEN THE ACFT WAS POWERED BACK UP AFTER LANDING THE AMBER GOV LIGHT EXTINGUISHED AND NO FURTHER CODES DETECTED. CHECKED RIGGING AND OPERATION OF COLLECTIVE POTENTIOMETER IAW MET 76.00.00.502, SEC 5.4 WITH NO FAULT FOUND. CONTACTED TECH REP TO VERIFY FAILURE AND IT WAS NOTED THAT THERE ARE SEVERAL OCCURRENCES WITH THIS FAILURE OUT IN THE FIELD. THERE IS A POSSIBLE EMI PROBLEM WITH THE WIRE BUNDLE DUE TO THE FACT THAT IT IS THE SAME BUNDLE THAT THE AIR-CONDITIONING WIRING IS LOCATED. WE ARE CURRENTLY WORKING WITH INTEGRATED FLIGHT SYS ON AN INSTALLATION OF AN EMI FILTER THAT GOES IN LINE ON THE CONDENSER BLOWER MOTOR. ACFT PERFORMED A GROUND RUN AND OPS CHECK FLIGHT WITH NO DEFECTS NOTED, AND RTS.