N253AM
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 Corp. (QMLA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
11 reports on file, 2010-10-23 – 2026-07-10.
Part: FADEC — FAILED (ZONE) · airframe 7,175 hrs · 25,394 cycles
NR 1 FADEC FAILURE IN FLIGHT
Part: TAIL BOOM — CRACKED (ZONE 200) · airframe 5,681 hrs · 19,977 cycles
DURING 1000-HOUR INSPECTION, A CRACK WAS DISCOVERED ON TAIL CONE UPPER FRAME 7 (PN: L533M1022215) ON THE FLANGE. THE CRACK MEASURES APPROXIMATELY 0.30â LONG.
Part: FRAME — CRACKED (ZONE 200) · airframe 5,681 hrs · 19,977 cycles
DURING 1000-HOUR INSPECTION, CRACK DAMAGE WAS DISCOVERED ON THE FRAME # 5A AT FUSELAGE STATION 5,023MM. TWO CRACKS WERE LOCATED AT THE FLANGE RADIUS WHERE THE FRAME MEETS THE OUTER STRUCTURE AT THE UPPER LH AND RH SIDES.
Part: KEELBEAM — CORRODED (ZONE 100) · airframe 5,681 hrs · 19,977 cycles
DURING 1000-HOUR INSPECTION, FOUND THE LEFT SIDE KEEL BEAM CAP (PN: L533M1009203) AT APPROXIMATE FUSELAGE STATION 2,585MM AND LBL 500MM WAS FOUND TO HAVE CORROSION DAMAGE AT THE NUT PLATE SECURING THE CABIN FLOOR.
Part: FRAME — CRACKED (ZONE 200) · airframe 5,681 hrs · 19,977 cycles
DURING A SCHEDULED INSPECTION REQUIRED BY AIR METHODS ASB21-01, DAMAGE WAS DISCOVERED AT FRAME 5 AT APPROXIMATELY FS 4,709MM RELATING TO THE AIR METHODS STC # SR00566DE â DRAWING 739-1600 â âINSTALLATION, MEDICAL WALLâ ON FAA FORM 337 DATED 16 OCT 2008. THE DAMAGE IS ADJACENT TO THE MEDICAL WALL ATTACH FITTING LOCATIONS. THE DESCRIPTION OF THE DAMAGE, SUBSTANTIATING DATA, AND REPAIR PROCEDURES PERFORMED ARE DOCUMENTED IN AIR METHODS ALERT SERVICE BULLETIN ASB21-01, REVISION A.
Part: PROFILE — CRACKED (ZONE 200) · airframe 5,681 hrs · 19,977 cycles
DURING 1000-HOUR INSPECTION, FOUND THE SPARE PART A-PROFILE LH FRAME AT APPROXIMATELY FS 4,800MM, WATER LINE 2,700MM, LEFT BUTT LINE 100MM WAS FOUND TO BE CRACKED ALL THE WAY THROUGH.
Part: KEELBEAM — CORRODED (ZONE 100) · airframe 4,686 hrs · 16,543 cycles
CORROSION WAS NOTED ON THE RT KEEL BEAM CAP P/N L533M1009203 AT FS 3150. THE DAMAGE WAS REPAIRED VIA REPAIR DOUBLER TO REINFORCE THE DAMAGED AREA IN ACCORDANCE WITH AIRBUS RDAS AHI 135 53 046 20 REV A DATED 15-OCT-2020.
Part: KEELBEAM — CORRODED (ZONE 100) · airframe 4,686 hrs · 16,543 cycles
CORROSION WAS NOTED ON THE LT KEEL BEAM CAP P/N L533M1009203 AT FS 5700. THE DAMAGE WAS REPAIRED VIA REPAIR DOUBLER TO REINFORCE THE DAMAGED AREA IN ACCORDANCE WITH AIRBUS RDAS AHI 135 53 044 20 REV A DATED 8-OCT-2020.
Part: CONTROL ROD — CRACKED (FLT CONTROLS) · airframe 4,686 hrs · 16,543 cycles
MULTIPLE CRACKS FOUND ON THE LONGITUDINAL SAS CONTROL ROD P/N: L221M1041104 AT THE 11 O`CLOCK POSITION (IF LOOKING AFT). ONE CRACK BEGINS AT A RIVET LOCATION AND CONTINUES PAST AN ADJACENT RIVET. THE SECOND CRACK PROPAGATES FROM THE EDGE OF THE TUBE PORTION, WHERE THE ROD END ATTACHMENT SECTION IS LOCATED. THESE CRACKS WERE DISCOVERED DURING A SCHEDULED 1000 HOUR AIRFRAME INSPECTION DURING THE PORTION OF THE INSPECTION THAT IS SPECIFIC TO FLIGHT CONTROLS.
Part: TORSION BAR — MISMANUFACTURED (TAIL ROTOR HEAD) · airframe 984 hrs · 3,278 cycles
THIS WAS A NEW PART AND WAS BEING INSTALLED INTO THIS TAIL ROTOR HEAD. BORE HOLE MISALIGNED, LAMINATES BUCKLES WHEN PARTS ARE INSTALLED.
Part: CONNECTOR — BURNED (EVAPORATOR) · airframe 808 hrs
MED CREW DETECTED A BURNED RUBBER/PLASTIC ODOR COMING FROM CABIN AIR CONDITIONING VENT. MECHANIC FOUND CONNECTOR SHORTED AND BURNED. REMOVED CONNECTOR AND WIRED AFT FAN MOTOR DIRECT WITHOUT CONNECTOR THROUGH ENVIROMENTAL SPLICES.