- Registered owner
- Air Methods LLC
- Location
- Greenwood Village, CO
- Owner type
- LLC
- Serial number
- 0480
- Year built
- 2006
- Type
- Rotorcraft
- Engine
- Turbo-shaft
- Airworthiness
- Standard, normal
- Airworthiness date
- June 6, 2016
- Certificate issued
- November 28, 2011
- Expires
- November 30, 2027
- Mode S code
- A08EFA
Eurocopter Deutschland EC 135 P2+TCDS H88EUAirframe · Eurocopter Deutschland EC 135 P2+TCDS E42NEEngine · Pratt & Whitney Canada PW206B2
From the FAA registry file of October 24, 2026.
On this page
Airworthiness directives that may apply · 50
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 |
|---|---|
| 2008 | 2 |
| 2009 | 2 |
| 2012 | 4 |
| 2013 | 7 |
| 2014 | 6 |
| 2015 | 1 |
| 2016 | 2 |
| 2017 | 1 |
| 2018 | 2 |
| 2019 | 4 |
| 2020 | 1 |
| 2021 | 11 |
| 2022 | 7 |
| 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 N135NKMatched 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 N135NKMatched 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 · 13
Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model.
SDR 2A6R2025090374105Seat Track · corrodedDURING 1000-HOUR INSPECTION, CORROSION WAS DISCOVERED ON THE MIDDLE TWO SEAT TRACKS OF THE CABIN FLOOR AT THE FAR AFT END. THE DAMAGE WAS REMOVED AND INSPECTED PER AMC ENGINEERING AUTHORIZATION # 23-5300-EA-5279, DATED 23 SEP 2025.SDR 2A6R2025082974104Xmsn Deck · canningDAMAGE WAS DISCOVERED TO THE TRANSMISSION DECK PANEL (PN: L533M1017293) IN THE FORM OF AN AREA OF DEFORMATION AND OIL CANNING. THE DAMAGE AREA IS LOCATED AT THE FORWARD PART OF THE MAIN TRANSMISSION OPENING IN THE DECK PANEL, AND IS REPORTED TO BE IN AN AREA ASDR 2A6R2025082874103Floor Skin · damagedDURING A 1000 HOUR INSPECTION, MULTIPLE AREAS OF DAMAGE WERE DISCOVERED TO THE COCKPIT FLOOR UPPER SKIN PANEL (P/N: L533M1014217) IN THE FORM OF DENTS AND CORROSION. A REPAIR PROCEDURE WAS PERFORMED IAW AIRBUS RDAS-EC135-53-2025-2881 REV A DATED 2025-09-16.SDR 2A6R2025082774106Cap · crackedDURING A 1000 HOUR INSPECTION, DAMAGE WAS FOUND IN THE FORM OF A 0.250'”CRACK LOCATED ON THE MAIN ROTOR HUB CAP PN: L662C1024101. A REPAIR PROCEDURE WAS PERFORMED IAW AIR METHODS EA# 23-5300-EA-5277 DATED 19 SEP 2025. REFERENCE MG741 ON FILE AT REPAIR STATIOSDR 2A6R2025082774102Frame · crackedDAMAGE WAS DISCOVERED ON THE TAIL CONE UPPER FRAME 7 (PN: L533M1022215) IN THE FORM OF A CRACK IN THE RADIUS ADJACENT TO THE SKIN FLANGE ON THE RH SIDE. THE CRACK MEASURES APPROXIMATELY 0.20'' IN LENGTH. A REPAIR PROCEDURE WAS PERFORMED IAW AMC EA# 23-5300-EASDR 2A6R2025082774101Profile · crackedDURING A 1000 HOUR INSPECTION, A CRACK WAS FOUND ON THE LH A-PROFILE (P/N: L533M1017375) UNDER THE TRANSMISSION DECK MEASURING .3'' IN LENGTH AND FORMS 6.1'' FROM THE FORWARD EDGE OF THE PART. A REPAIR PROCEDURE WAS PERFORMED IAW AIRBUS RDAS-EC135-53-2025-286SDR QMLA2023122220118Dimmer · unknown(PILOT)--INSTRUMENT LIGHTS FLICKERED AND THEN WENT OUT. A CREWMEMBER REPORTED BRIEFLY SMELLING AN ELECTRICAL ODOR. (MECH). - NEW CONTROLLER IS ORDERED ON MR-089354-23. I (DON TOLAR) DIDN'T NOTICE ANY RESIDUAL BURNT SMELL, WHILE ACCESSING DIMMER CONTROL AREA, SDR 2A6R2023120669204Keelbeam · corrodedDAMAGE WAS NOTED TO THE LH KEEL BEAM CAP (PN: L533M1009203), AS WELL AS THE RH KEEL BEAM CAP (PN: L533M1010203), IN THE HORIZONTAL FLANGE IN THE FORM OF SEVERAL AREAS OF CORROSION. FOUR AREAS OF CORROSION WERE IDENTIFIED IN THE LH KEEL BEAM CAP, AND FOUR AREASSDR 2A6R2023120669203Frame · crackedDAMAGE TO THE RH FRAME 5 ANGLE (PN: L533M1105218) IN THE FORM OF CRACK DAMAGE IN THE UPPER SECTION OF THE ANGLE, AS WELL AS CRACK AND DEFORMATIONS ON THE RH FRAME 5 SHEET (PN: L533M1105219) ON THE INBOARD FLANGE.SDR 2A6R2023120669201Frame · corrodedCORROSION DAMAGE WAS NOTED TO THE FRAME 3 T-CAP (PN: L533M1028203) UNDER THE FORWARD HORIZONTAL FLANGE NUTPLATES AT APPROXIMATELY FS3150MM LBL500MM-RBL500MM.SDR QMLA2023092820079Bypass Valve · faultedWHILE PERFORMING INSTRUMENT AND SYSTEMS SCAN, I REALIZED THAT ENGINE #2 OIL TEMP WAS 131 AND CLIMBING WHILE KNOWING THE LIMIT IS 129.5. I ESTABLISHED THE AIRCRAFT INTO AN OEI CONFIGURATION AND PLACED THE #2 ENGINE INTO IDLE POSITION. SAFE CONFIGURATION WAS MAISDR 2A6R2023120669202Frame · corrodedTHE FORWARD LOWER SIDE OF THE FRAME 3 BULKHEAD AT APPROXIMATELY FUSELAGE STATION 3,150MM, WATER LINE 1,150MM WAS FOUND TO HAVE CORROSION DAMAGE ALONG THE BOTTOM EDGE OF THE WEB BETWEEN LBL250 – RBL250.SDR QMLA2020012203203Frame · crackedFRAME 5A CRACKED. INSTALLED DOUBLER P/N L533M1022966 PER SB EC135-53-031. AIRCRAFT IS CURRENTLY OUT OF SERVICE.
STCs that may be installed · 74
Approved for this aircraft’s airframe or engine model. The registry doesn’t record which STCs an aircraft has; its records do.