N332AM
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
A LARGE DENT WAS DISCOVERED ON THE TRANSMISSION DECK SKIN AND CENTER BEAM PN: 355A21-2109-21. THE DAMAGE TO THE DECK SKIN IS APPROXIMATELY 0.060â DEEP AND 3.5â WIDE BY 2.5â LONG. THE DAMAGE TO THE CENTER BEAM HAS AN AREA OF 2.0â WIDE AND 1.3â HIGH ON THE VERTICAL WEB AFFECTING THE ENTIRE UPPER FLANGE. AN APPROXIMATE LOCATION OF THE DAMAGE IS AT F.S. 3541MM, W.L. -1765MM, AND L.B.L. 0MM. A DETAILED DESCRIPTION OF THE TYPICAL DAMAGE REPAIR AND APPROVED REPAIR PROCEDURES ARE PROVIDED IN AIR METHODS ENGINEERING AUTHORIZATION 17-5330-EA-5613, INITIAL REVISION DATED 17 APR 2026 AND IS SUBSTANTIATED BY FAA FORM 8110-3, SEQUENCE # 26RL013AM BY RYAN D. LEE DER: 905240204.
DAMAGE TO THE RH EDGE FRAME (PN: 350A21-4915-22), IN THE FORM OF CORROSION, WAS IDENTIFIED ON THE OUTBOARD FACE OF THE FRAME. THE RH EDGE FRAME WAS PARTIALLY REPLACED AND SPLICED INTO THE REMAINING SERVICEABLE FRAME. A DETAILED DESCRIPTION OF THE APPROVED REPAIR/INSTALLATION PROCEDURES IS PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-EC130-53-2024-0040, ISSUE A DATED 09 JAN 2024, AND AC 43.13-1B CHAPTER 4, SECTION 4, PARAGRAPH 4-57 CHANGE 1 DATED 9/8/98.
DAMAGE TO THE LH EDGE FRAME (PN: 350A21-4913-22), IN THE FORM OF CORROSION, WAS IDENTIFIED ACROSS THE ENTIRE LENGTH OF THE OUTBOARD FACE OF THE FRAME. THE LH EDGE FRAME REQUIRED FULL REPLACEMENT; THEREFORE, CUTS OR SPLICING DOUBLERS WERE NOT REQUIRED. A DETAILED DESCRIPTION OF THE APPROVED REPAIR/INSTALLATION PROCEDURES IS PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-EC130-53-2024-0040, ISSUE A DATED 09 JAN 2024, AND AC 43.13-1B CHAPTER 4, SECTION 4, PARAGRAPH 4-57 CHANGE 1 DATED 9/8/98.
A DENT WAS DISCOVERED ON THE TRANSMISSION DECK SKIN ON THE LH SIDE. THE DAMAGE IS APPROXIMATELY 0.038â DEEP AND 0.5â IN DIAMETER. AN APPROXIMATE LOCATION OF THE DAMAGE IS AT F.S. 3661MM, W.L. -1765MM, AND L.B.L. -450MM. A DETAILED DESCRIPTION OF THE TYPICAL DAMAGE REPAIR AND APPROVED REPAIR PROCEDURES ARE PROVIDED IN AIR METHODS ENGINEERING AUTHORIZATION 17-5330-EA-5485, INITIAL REVISION DATED 02 MAR 2026.
AFTER AMBER AND RED GOV LIGHT ILLUMINATED, MYSELF AND THE CREW COULD SMELL AN ELECTRICAL SMOKE ODOR. AFTER LANDING AND SHUTDOWN. ARRIVED AT AIRCRAFT, CLEANED ELECTRICAL CONNECTORS ON FADEC AND NF SENSOR. GOV LIGHT WENT OUT.
UPON DEPARTURE FROM KPDK, ENG CHIP LIGHT ILLUMINATED ON THE WARNING PANEL. IT WENT OUT AFTER A FEW SECONDS. LANDED AS SOON AS POSSIBLE BACK TO KPDK AND SHUT DOWN ENGINE, CHECKED THE CHIP PLUGS AND THERE WAS NOTHING ON THEM. GROUND RUN THE AIRCRAFT WITH NO LIGHT. RETURNED TO SERVICE.
DURING A SCHEDULED MX EVENT FOR AAIP INSPECTION, A1040 300 HOUR / 12 MONTH INSPECTION, THE HORIZONTAL STABILIZER WAS PULLED. THE INSPECTION WAS PERFORMED ON THE INTERIOR OF THE TAIL BOOM & THE MOUNTING BRACKETS FOR THE HORIZONTAL STABILIZER. THE UPPER RT MOUNT IS CRACKED & WILL NEED TO BE REPLACED BY MFG DUE TO THE NATURE OF THE REPAIR.
DEPARTED BASE, APPROX 5 NM FROM HOSPITAL NOTICED THAT THE BACK LIGHTING FOR ALL THE INSTRUMENTS WAS DIMMING. TRIED TO INCREASE THE LIGHTING BUT WAS UNABLE. THE NEXT THING TO HAPPEN WAS THE RADAR ALT. WAS INDICATING 0 FEET & WARNING LIGHT ILLUMINATING, WAS AIDED FLIGHT NVG'S. LOOKED BOTH OUTSIDE & AT THE BACKUP ALT & NOTED AT 3300+ FEET WELL ABOVE THE 1884 REQUIRED FOR THE EN-ROUTE ATL NEEDED TO AVOID ALL OBSTACLES. THE NR 2 GPS WENT OFF LINE FOLLOWED BY THE GYRO'S SHUTDOWN, SHORTLY AFTER THE NR 1 GPS SHUTDOWN & THE VEMD & THE REST OF THE ACFT LIGHTS. DURING THE ENTIRE TIME THERE WAS NO CAUTION WARNING PANEL LIGHT TO SHOW THAT THERE WAS ANY MALFUNCTION, GENE, WARNING. LANDED SAFELY AT THE HOSPITAL HELO-PAD, DURING SHUTDOWN WAS UNABLE TO PLACE THE THROTTLE INTO THE IDLE POSITION BEFORE SHUTDOWN.
DURING INSPECTION FOR CRACKS IAW AD 2014-12-51, A CRACK WAS FOUND IN THE LOWER RT DOUBLER PLATE FOR THE HORIZONTAL STABILIZER ON THE INTERIOR OF THE TAIL BOOM. THE INSPECTION OF THIS AREA DOES NOT FALL WITHIN THE SCOPE OF THE APPLICABLE AD. THE CRACK IS APPROX 1/2 INCH LONG RADIATING FROM A RIVET HOLE UPWD & FWD IN A DIAGONAL DIRECTION TO THE OPENING OF THE TAIL BOOM WHERE THE TE OF THE HORIZONTAL STABILIZER PASSES THROUGH THE TAIL BOOM. THE CRACK ALSO RADIATES IN THE OPPOSING DIRECTION ABOUT 1/4 INCH & IS NO LONGER VISIBLE BECAUSE THE LOWER HORIZONTAL STRUCTURAL MEMBER THAT IS MOUNTED UNDER THE HORIZONTAL STABILIZER COVERS THE AREA.