- Registered owner
- Air Methods LLC
- Location
- Greenwood Village, CO
- Owner type
- LLC
- Serial number
- 0453
- Type
- Rotorcraft
- Engine
- Turbo-shaft
- Certificate issued
- July 3, 2014
- Expires
- July 31, 2027
- Mode S code
- A6C050
From the FAA registry file of October 24, 2026.
On this page
Airworthiness directives that may apply · 48
Matched by this aircraft’s airframe and engine models. Each AD’s applicability may narrow it by serial number, part number or equipment.
| 2000 | 1 |
|---|---|
| 2004 | 1 |
| 2008 | 2 |
| 2009 | 1 |
| 2012 | 4 |
| 2013 | 7 |
| 2014 | 5 |
| 2015 | 1 |
| 2016 | 2 |
| 2017 | 1 |
| 2018 | 2 |
| 2019 | 4 |
| 2020 | 1 |
| 2021 | 11 |
| 2022 | 6 |
| 2024 | 4 |
| 2025 | 3 |
| 2026 | 5 |
Airframe · Eurocopter Deutschland EC 135 P2
AD 2026-20-06Main rotor gearboxAD 2026-17-05Cabin Equipment/FurnishingsAD 2026-08-10Passenger compartment equipmentInformation bulletins that may apply · 3
Advisory, not mandatory.
NTSB investigations
No NTSB investigations matched to N534LNMatched by N-number and event date, checked against the reported serial number, make and model. Investigations from before this aircraft carried the mark are under Earlier aircraft. Investigations on Eurocopter Deutschland EC 135 P2 aircraft
FAA incident reports
No FAA accident or incident reports matched to N534LNMatched by N-number and event date, checked against the reported make and model. Reports from before this aircraft carried the mark are under Earlier aircraft. Reports on Eurocopter Deutschland EC 135 P2 aircraft
Service difficulty reports · 14
Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model.
SDR QMLA2024092420124Gearbox · making metalMAIN TRANSMISSION CHIP LIGHT DETECTOR ILLUMINATED. OIL PRESSURE STEADYSDR 2A6R2024082971108Deck Plate · corrodedFASTENER HOLE DAMAGE WAS DISCOVERED ON THE TRANSMISSION DECK PANEL (PN: L533M1017293) UNDER THE AFT OUTBOARD SECTION OF THE RH XY FITTING. A DETAILED DESCRIPTION OF THE DAMAGE AND AN APPROVED REPAIR PROCEDURE IS PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEETSDR 2A6R2024082971107Skin · corrodedCRACK DAMAGE WAS DISCOVERED ON THE TAIL CONE SKIN (PN: L533M1022262) ON THE RH SIDE. A DETAILED DESCRIPTION OF THE DAMAGE AND AN APPROVED REPAIR PROCEDURE IS PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-EC135-53-2024-1344, ISSUE A DATED 06 MAY 2024.SDR 2A6R2024082971106Keelbeam · corrodedNOTE: PLEASE LIMIT YOUR DESCRIPTION TO 1500 CHARACTERS) DAMAGE WAS NOTED TO THE RH KEEL BEAM CAP (P/N: L533M1010203) HORIZONTAL FLANGE IN THE FORM OF SEVERAL AREAS OF CORROSION. THE AREA WAS REPAIRED VIA REINFORCING REPAIR DOUBLER IAW AIRBUS RDAS-EC135-53-2024SDR 2A6R2024082971105Fitting · corrodedCORROSION DAMAGE WAS DISCOVERED ON THE LH FORWARD LANDING GEAR FITTING (PN: L533M1006228) ON THE INBOARD SURFACE AT THE LOWER EDGE OF THE CENTER SECTION OF THE FITTING. A DETAILED DESCRIPTION OF THE DAMAGE AND AN APPROVED REPAIR PROCEDURE IS PROVIDED IN AIRBUSDR 2A6R2024082971104Angle · corrodedCORROSION DAMAGE WAS DISCOVERED ON THE LOWER ANGLE (PN: L311M1060235) AT APPROXIMATELY FUSELAGE STATION 1,730MM. REPLACEMENT PARTS WERE NOT AVAILABLE; THEREFORE, A REPLACEMENT ANGLE WAS FABRICATED OUT OF 0.080” 2024-T3511 PER AIR METHODS ENGINEERING AUTHORIZASDR 2A6R2024082971103Frame · corrodedCORROSION DAMAGE WAS DISCOVERED ON FRAME 3 (PN: L533M1028221) AND ON THE FRAME 3 UPPER T CAP (PN: L533M1028203) AT APPROXIMATELY FUSELAGE STATION 3,150MM. REPLACEMENT PARTS WERE NOT AVAILABLE; THEREFORE, A REPLACEMENT FRAME AND T CAP WERE FABRICATED OUT OF 0SDR 2A6R2024082971102Frame · corrodedCORROSION DAMAGE WAS DISCOVERED ON THE LOWER ANGLE (PN: L533M1043427) AT APPROXIMATELY FUSELAGE STATION 2,675MM. REPLACEMENT PARTS WERE NOT AVAILABLE; THEREFORE, A REPLACEMENT ANGLE WAS FABRICATED OUT OF 0.050” 2024-T3 PER AIR METHODS ENGINEERING AUTHORIZATIOSDR QMLA2018062981075Actuator · stuckPICKED UP THE HELICOPTER IN A HOVER FOR A MAINTENANCE CHECK FLIGHT AND HOVERED OVER TO THE GRASS AREA BETWEEN THE RAMP AND TAXI WAY, CHECKED FLIGHT CONTROLS FOR NORMAL MOVEMENT AND THEN HOVERED TAXIED TO THE RUNWAY FOR A NORMAL DEPARTURE. MADE A LEFT TURN FORSDR QMLA2013010313003Chip Detector · failedPILOT REPORT. UPON START OF ENGINES 1 & 2 AND AT GROUND IDLE, HAD A TRANSMISSION CHIP CAUTION LIGHT ILLUMINATED. SHUTDOWN ACFT, NOTIFIED MECHANIC(S) AND COMM CENTER OF AIRCRAFT STATUS. APPROX. 1800 LOCAL TIME WAS DETERMINED ACFT COULD NOT BE RETURNED TO SERSDR QMLA2012122112194Transmission · making metalDURING SHUTDOWN OF AC TRANSMISSION CHIP LIGHT ILLUMINATED. CHIP PLUG WAS INSPECTED AND FOUND A SLIGHT STRAN OF DEBRIS. INSPECTED FILTER ASSY AND FOUND NO UNUSUAL CONTAMINATION. ELECTED TO REPLACE THE FILTER. ALL WORK WAS PERFORMED IAW EC 135-63A-012, REV 5SDR QMLA2012060212091Connector · looseWHILE ENROUTE, APPROX 10 MINUTES INTO THE FLIGHT, THE NR 1 GEN DISCONNECTED LIGHT ILLUMINATED ON THE CAD. COMPLETED THE EMERGENCY PROCEDURE IAW THE RFM. THE GENERATOR WOULD NOT RESET. PLACED THE NR 1 GENERATOR ON THE OFF POSITION AND REDUCED ALL NON-ESSENTIASDR QMLA2011061911069Bearing · bindingDURING PRE FLIGHT, THE PILOT FOUND THAT WHEN HE TURNED THE TAIL ROTOR IN THE DIRECTION OF ROTATION HE HEARD A POPPING NOISE COMING FROM THE TAIL ROTOR DRIVE SHAFT. UPON FURTHER INSPECTION FOUND THAT ONE OF THE BEARINGS THAT HOLDS THE TAIL ROTOR DRIVE SHAFT WASDR 45302172008Converter · burnedDURING A HEMS FLIGHT WITH PATIENT ON BOARD, THE CREW SMELLED AN ELECTRICAL BURNING ODOR. THE AC WAS LANDED SAFELY. OTHER TRANSPORT WAS ARRANGED AND MAINT CALLED. THE ONLY FAILURE THE MECHANIC FOUND WAS A 110 VAC TO 28 VDC CONVERTER, THAT WAS USED WITH THE I
STCs that may be installed · 72
Approved for this aircraft’s airframe or engine model. The registry doesn’t record which STCs an aircraft has; its records do.