N355CF
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, 2018-07-06 – 2025-02-26.
Part: UNKNOWN — VIBRATION · airframe 5,131 hrs · 16,839 cycles
VIBRATION IN SEAT AND PEDALS
Part: BULKHEAD WEB — CHAFED (ZONE 100) · airframe 3,878 hrs · 10,511 cycles
DAMAGE TO THE AFT BULKHEAD WEB (PN: 350A21-1036.60) WAS NOTED IN THE FORM OF NUMEROUS CHAFES. THE CHAFES WERE MEASURED TO BE ON AVERAGE 0.50" IN LENGTH WITH THE DEEPEST CHAFE BEING 0.008" DEEP.
Part: TAIL BOOM — DENTED (TAIL BOOM) · airframe 3,878 hrs · 10,511 cycles
DAMAGE TO THE TAIL BOOM AFT SKIN PANEL (PN: 350A23-0020.22). THE CREASE AND GOUGE DAMAGES WERE DISCOVERED TO BE JUST FORWARD OF THE TAIL ROTOR GEAR BOX. THE CREASE DAMAGE IS APPROXIMATELY 0.40" WIDE AND THE GOUGE DAMAGE IS APPROXIMATELY 0.10" IN LENGTH, 0.05" IN WIDTH AND 0.020" IN DEPTH. DAMAGE WAS ALSO REPORTED TO THE TAIL BOOM SKIN UPPER FWD PANEL (PN: 350A23-0020.21 ). THE DENT DAMAGE IS FOUND ON THE AFT SIDE OF THE RH SKIN UPPER FWD PANEL. THE DENT DAMAGE IS APPROXIMATELY 1.50" IN LENGTH, 1.20" IN WIDTH AND 0.029" DEPTH.
Part: NONE — USED (ZONE 400) · airframe 3,878 hrs · 10,511 cycles
CUSTOMER HAS REPORTED DAMAGE TO THE TAIL BOOM AFT SKIN PANEL (PN: 350A23-0020.22). THE CREASE AND GOUGE DAMAGES WERE DISCOVERED TO BE JUST FORWARD OF THE TAIL ROTOR GEAR BOX. THE CREASE DAMAGE IS APPROXIMATELY 0.40â WIDE AND THE GOUGE DAMAGE IS APPROXIMATELY 0.10â IN LENGTH, 0.05â IN WIDTH AND 0.020â IN DEPTH
Part: NONE — USED (ZONE 200) · airframe 3,878 hrs · 10,511 cycles
CUSTOMER HAS REPORTED DAMAGE TO THE AFT BULKHEAD WEB (PN: 350A21-1036.60) IN THE FORM OF NUMEROUS CHAFES. THE CHAFES WERE MEASURED TO BE ON AVERAGE 0.50â IN LENGTH WITH THE DEEPEST CHAFE BEING 0.008â DEEP.
Part: BULKHEAD — USED (ZONE 200) · airframe 3,878 hrs · 10,511 cycles
DAMAGE TO THE 15° BULKHEAD LH POST (PN: 350A21-1031.33) WAS NOTED IN THE FORM OF CHAFING. THE CHAFING DAMAGE IS APPROXIMATELY 0.40â IN LENGTH, 0.07â IN WIDTH AND 0.017â IN DEPTH.
Part: SUPPORT — CHAFED (TXMSN DECK) · airframe 3,279 hrs · 8,400 cycles
CHAFING ON THE TRANSMISSION DECK SUPPORT (350A21-1041-143) THAT IS .5â BY .2â AND .013â AT ITS DEEPEST POINT
Part: FRAME — CHAFED (ZONE 200) · airframe 3,279 hrs · 8,400 cycles
CHAFING ON THE LT X-FRAMES AFT UPPER AND LOWER LEGS. THE AFT UPPER LEG DAMAGE IS .24â BY .22â AND IS .024â AT ITS DEEPEST POINT LOCATED AT STA 3650, WL 1979, AND BL 430L. THE AFT LOWER LEG DAMAGE IS .74â BY .19â AND MEASURES .002â LOCATED AT STA 3650, WL 2305, AND BL 430L.
Part: FLOOR PANEL — CORRODED (BS 1000-1550) · airframe 3,279 hrs · 8,400 cycles
CORROSION WAS DISCOVERED ON THE RT HAND SIDE CABIN FLOOR EDGE SECTION AIRBUS PN 350A21-1359 RANGING FROM STA 1000 TO 1550.
Part: SKIN — CHAFED (TAIBOOM) · airframe 3,279 hrs · 8,400 cycles
CHAFING ON THE RT INTERIOR SIDE OF THE TAILBOOM SKIN LOCATED AT APPROXIMATELY STA 7898, WL 2089, AND BL 90R JUST FORWARD OF THE HORIZONTAL STABILIZER OPENING. THE CHAFE IS .95â BY .12â AND IS .007â AT ITS DEEPEST POINT.
Part: FRAME — CHAFED · airframe 2,445 hrs · 5,870 cycles
CHAFING FOUND ON LF X FRAME. BLENDED OUT DAMAGE IAW RDAS-AHI 350-53-030-18.