N831ME
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 |
|---|---|---|---|
| CENTER FOR EMERGENCY MEDICINE OF WESTERN PA INC (E3MA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
DENTS AND LOCALIZED DELAMINATION WERE FOUND ON THE UNDERSIDE SKIN OF THE CABIN FLOOR, MEASURING UP TO 89 MM Ã 914 MM (3.5 IN Ã 36 IN) AND 50 MM Ã 610 MM (2 IN Ã 24 IN). REPAIRED IN ACCORDANCE WITH AIRBUS HELICOPTERS RDAS RDAS EC135 53 2026 2040A, ISSUE DATE 11 JUN 2026. THE REPAIR INCLUDED REMOVAL OF DAMAGED SKIN, INSPECTION AND REPAIR OF HONEYCOMB CORE AS REQUIRED, AND INSTALLATION OF AN ALUMINUM UNDERSIDE SKIN DOUBLER BONDED AND CURED PER APPROVED DATA. SURFACE PROTECTION AND FINISH WERE RESTORED. REPAIR INSPECTED BY VISUAL AND TAP TEST AND FOUND SATISFACTORY.
POST REMOVING DAMAGED TEFLON LINER ON BLADE. DISCOVERED CRACK ON WEDGE ON WEDGE OF UPPER TRAILING BUSH HOLE TO OUTER ROVING LOOP.
DAMAGE 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 PROCEDURES ARE PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-EC135-53-2026-1925, ISSUE A.
DURING 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 R.B.L. 50MM. A DETAILED DESCRIPTION OF THE DAMAGE REPAIR AND APPROVED REPAIR PROCEDURES ARE PROVIDED IN AIR METHODS ENGINEERING AUTHORIZATION 23-5300-EA-5655, INITIAL REVISION DATED 18 MAY 2026 AND IS SUBSTANTIATED BY FAA FORM 8110-3,
#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 AN AUTOPILOT WARNING LIGHT AND THE AUTOPILOT TURNED OFF. CONTINUED THE ILS APPROACH WITH THE AUTOPILOT IN OFF MODE AND BY USING #2 VHF RADIO TO COMMUNICATE WITH CENTER. 07/25 RML NOTE: COULD NOT DUPLICATE AUTO PILOT FAULT ON GROUND AND NO DISCREPANCIES NOTED DURING T/S. COULD NOT MOC FLIGHT DUE TO WEATHER. WILL PERFORM FUNCTIONAL CHECKS THIS MORNING. PERFORMED MULTIPLE FUNCTION CHECKS. THIS AIRCRAFT HAS BEEN RETURNED TO REVENUE SERVICE, REF # MEC-012816.
DAMAGE 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 APPROXIMATELY 1.625" ON THE FWD L/H SIDE OF THE FRAME 5 UPPER MOUNT LOCATION OF THE MEDICAL WALL. CRACKS WERE ALSO DISCOVERED ON BOTH L/H AND R/H FRAME 5 ANGLES (P/N: L533M1088218/L533M1105218) AT THE AFT INBOARD LOWER ATTACHMENT POINT OF THE MEDICAL STC. THE L/H ANGLE CRACKED MEASURED APPROXIMATELY 1.05", WITH THE R/H CRACK MEASURING 1.0" IN LENGTH.
DAMAGE 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 1.0â X 0.50â AND 0.020â DEEP. CORROSION AT LOCATION 2 MEASURED AT APPROXIMATELY 0.70â X 0.50â AND 0.027â DEEP.
DAMAGE 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 APPROXIMATELY 1.625" ON THE FWD L/H SIDE OF THE FRAME 5 UPPER MOUNT LOCATION OF THE MEDICAL WALL. CRACKS WERE ALSO DISCOVERED ON BOTH L/H AND R/H FRAME 5 ANGLES (P/N: L533M1088218/L533M1105218) AT THE AFT INBOARD LOWER ATTACHMENT POINT OF THE MEDICAL STC. THE L/H ANGLE CRACKED MEASURED APPROXIMATELY 1.05", WITH THE R/H CRACK MEASURING 1.0" IN LENGTH
DAMAGE 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 APPROXIMATELY 1.625" ON THE FWD L/H SIDE OF THE FRAME 5 UPPER MOUNT LOCATION OF THE MEDICAL WALL. CRACKS WERE ALSO DISCOVERED ON BOTH L/H AND R/H FRAME 5 ANGLES (P/N: L533M1088218/L533M1105218) AT THE AFT INBOARD LOWER ATTACHMENT POINT OF THE MEDICAL STC. THE L/H ANGLE CRACKED MEASURED APPROXIMATELY 1.05", WITH THE R/H CRACK MEASURING 1.0" IN LENGTH.
AUTOPILOT 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 ACTUATOR
A 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.