- Registered owner
- Air Methods LLC
- Location
- Greenwood Village, CO
- Owner type
- LLC
- Serial number
- 0493
- Year built
- 2006
- Type
- Rotorcraft
- Engine
- Turbo-shaft
- Airworthiness
- Standard, normal
- Airworthiness date
- May 11, 2009
- Certificate issued
- March 25, 2026
- Expires
- March 31, 2033
- Mode S code
- AB5D29
Eurocopter Deutschland EC 135 T2+TCDS H88EUAirframe · Eurocopter Deutschland EC 135 T2+TCDS E34NEEngine · Turbomeca ARRIUS-2B2
From the FAA registry file of October 24, 2026.
On this page
Airworthiness directives that may apply · 19
Matched by this aircraft’s airframe and engine models. Each AD’s applicability may narrow it by serial number, part number or equipment.
| 2005 | 1 |
|---|---|
| 2007 | 1 |
| 2008 | 2 |
| 2012 | 1 |
| 2013 | 2 |
| 2014 | 2 |
| 2015 | 1 |
| 2016 | 1 |
| 2018 | 1 |
| 2019 | 3 |
| 2021 | 1 |
| 2022 | 1 |
| 2023 | 1 |
| 2024 | 3 |
| 2025 | 4 |
| 2026 | 6 |
Airframe · Eurocopter Deutschland EC 135 T2+
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 N831MEMatched 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 T2+ aircraft
FAA incident reports
No FAA accident or incident reports matched to N831MEMatched 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 T2+ aircraft
Service difficulty reports · 11
Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model.
SDR 2A6R2026061575601Floor Skin · dentedDENTS AND LOCALIZED DELAMINATION WERE FOUND ON THE UNDERSIDE SKIN OF THE CABIN FLOOR, MEASURING UP TO 89 MM × 914 MM (3.5 IN × 36 IN) AND 50 MM × 610 MM (2 IN × 24 IN). REPAIRED IN ACCORDANCE WITH AIRBUS HELICOPTERS RDAS RDAS EC135 53 2026 2040A, ISSUE DATE 11SDR 2A6R2026060475601Liner · crackedPOST REMOVING DAMAGED TEFLON LINER ON BLADE. DISCOVERED CRACK ON WEDGE ON WEDGE OF UPPER TRAILING BUSH HOLE TO OUTER ROVING LOOP.SDR 2A6R2026060375601Keelbeam · corrodedDAMAGE WAS NOTED TO THE RH KEEL BEAM CAP (P/N: L533M1010203) HORIZONTAL FLANGE IN THE FORM OF SEVERAL AREAS OF CORROSION. THERE ARE REPORTED TO BE 3EA AREAS OF CORROSION IN THE RH KEEL BEAM CAP. A DETAILED DESCRIPTION OF THE DAMAGE AND APPROVED REPAIR PROCEDURSDR 2A6R2026052675601Deck Plate · dentedDURING 500-HOUR INSPECTION, A DENT WAS DISCOVERED ON THE R/H SIDE OF THE TRANSMISSION DECK (P/N: L533M1017295). THE MAXIMUM DEPTH IS APPROXIMATELY 0.022" WITH A MAXIMUM DIAMETER OF 0.8. AN APPROXIMATE LOCATION OF THE DAMAGE IS AT STA. 4600MM, W.L. 2465MM, AND SDR QMLA2025072620077Vhf Comm · faulted#1 VHF RADIO STOPPED TRANSMITTING. SHORTLY AFTER, DURING LEVEL FLIGHT, IFR, 6000MSL, 120KN, ON ATC VECTOR IN HEADING MODE AND THE NAV SOURCE IN ILS2, THE AUTOPILOT MADE AN UNCOMMANDED, ABRUPT LEFT TURN AND PITCH UP. THE MASTER
CAUTION ILLUMINATED ALONG WITH ASDR 2A6D20230321005Angle · crackedDAMAGE WAS FOUND TO THE FRAME 5 (P/N: L533M1088219/L533M1105219) IN THE FORM OF CRACKS. THERE ARE FOUR CRACKS TO BOTH THE L/H AND R/H FRAME NEAR THE UPPER AND LOWER MOST POINTS WHERE THE MEDICAL INTERIOR BEAM ATTACHES. THE LONGEST CRACK MEASURED TO BE APPROXIMSDR 2A6D20230321004Angle · crackedDAMAGE WAS FOUND TO THE FRAME 5 (P/N: L533M1088219/L533M1105219) IN THE FORM OF CRACKS. THERE ARE FOUR CRACKS TO BOTH THE L/H AND R/H FRAME NEAR THE UPPER AND LOWER MOST POINTS WHERE THE MEDICAL INTERIOR BEAM ATTACHES. THE LONGEST CRACK MEASURED TO BE APPROXIMSDR 2A6D20230321002Frame · crackedDAMAGE WAS FOUND TO THE FRAME 5 (P/N: L533M1088219/L533M1105219) IN THE FORM OF CRACKS. THERE ARE FOUR CRACKS TO BOTH THE L/H AND R/H FRAME NEAR THE UPPER AND LOWER MOST POINTS WHERE THE MEDICAL INTERIOR BEAM ATTACHES. THE LONGEST CRACK MEASURED TO BE APPROXIMSDR 2A6D20230321001Keel Fitting · corrodedDAMAGE WAS NOTED TO THE R/H KEEL BEAM CAP (P/N: L533M1010203) IN THE FORM OF 2 EA SPOTS OF CORROSION LOCATED BENEATH THE EDGE OF THE COCKPIT FLOOR. THE CORROSION AT LOCATION 1 MEASURED AT APPROXIMATELY 1.0” X 0.50” AND 0.020” DEEP. CORROSION AT LOCATION 2 MEASSDR E3MA201612070001Autopilot Sys · bindingAUTOPILOT FAILED PREFLIGHT TEST, AUTOPILOT ME LED. DURING TROUBLESHOOTING OF AUTOPILOT SYSTEM BY MAINTENANCE THE AIRCRAFT EXPERIENCED UNUSUAL VIBRATIONS/OSCILLATIONS IN THE HOVER CHECK. FOUND FAULTY ELECTRO HYDRAULIC ACTUATORSDR E3M2010F00001Bulkhead · crackedA 4 INCH CRACK WAS DISCOVERED ON THE BULKHEAD SKIN ADJACENT TO FRAME 5 (FR5), RT SIDE NEAR THE NR 2 ENGINE FACEC COMPUTER. THE CRACK WAS DISCOVERED WHEN THE PELICAN RACK WAS LOWERED DURING INSPECTION.
STCs that may be installed · 71
Approved for this aircraft’s airframe or engine model. The registry doesn’t record which STCs an aircraft has; its records do.