N135NK
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
DURING 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.
DAMAGE 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 APPROXIMATELY 2.1â X 3.1â IN SIZE. A REPAIR PROCEDURE WAS PERFORMED IAW AIRBUS RDAS-EC135-53-2025-2919 REV A DATED 2025-09-16.
DURING 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.
DAMAGE 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-EA-0480 DATED 09/08/2025.
DURING A 1000 HOUR INSPECTION, DAMAGE WAS FOUND IN THE FORM OF A 0.250'âCRACK 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 STATION CRS2A6R933B FOR DETAILS.
DURING 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-EC135-53-2025-2864- ISSUE A, DATED 2025-09-11.
(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, UNDER FLOOR PANEL AREA. NOR DID I NOTICE IT IN CABIN AREA.
DAMAGE 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 AREAS OF CORROSION WERE IDENTIFIED IN THE RH KEEL BEAM CAP.
CORROSION DAMAGE WAS NOTED TO THE FRAME 3 T-CAP (PN: L533M1028203) UNDER THE FORWARD HORIZONTAL FLANGE NUTPLATES AT APPROXIMATELY FS3150MM LBL500MM-RBL500MM.
DAMAGE 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.
WHILE 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 MAINTAINED, AND I NOTED #2 ENG OIL TEMP LOWERED INITIALLY BELOW LIMITS WHILE IN DESCENT, EVEN WITH THE #2 ENG AT IDLE, TEMPERATURE CONTINUED TO INCREASE. FEARING THAT IT WOULD REACH THE LIMIT YET AGAIN, I FOLLOWED THE EP CORRECTLY AND TURNED THE ENGINE OFF AND PERFORMED A SUCCESSFUL OEI LANDING AT KGVL. HELICOPTER NOW AWAITING FURTHER MAINTENANCE.
THE 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 â RBL250.
FRAME 5A CRACKED. INSTALLED DOUBLER P/N L533M1022966 PER SB EC135-53-031. AIRCRAFT IS CURRENTLY OUT OF SERVICE.