N639ME
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 |
| CENTER FOR EMERGENCY MEDICINE OF WESTERN PA INC (E3MA) | Operator | on 2015-11-06 | Operator named in NTSB report |
Accident & incident history
Operated by CENTER FOR EMERGENCY MEDICINE OF WESTERN (per NTSB report)
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.
5 reports on file, 2007-10-18 – 2024-11-21.
Part: FRAME — CORRODED (ZONE 100) · airframe 9,374 hrs · 39,449 cycles
CORROSION DAMAGE WAS DISCOVERED ON THE LOWER FLANGE OF FRAME 1 WEB (PN: L533M1011211) ON THE LH AND RH SIDES. A DETAILED DESCRIPTION OF THE DAMAGE AND AN APPROVED REPAIR PROCEDURE IS PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-EC135-53-2024-1990, ISSUE A DATED 26 JUN 2024.
Part: SKIN — CRACKED (ZONE 200) · airframe 9,374 hrs · 39,449 cycles
CRACK DAMAGE WAS DISCOVERED ON THE CENTER TAIL CONE SKIN (PN: L533M1022262) MEASURING APPROXIMATELY 0.60â. ADDITIONAL DAMAGE REQUIRING REPAIR IN THIS AREA DUE TO A DOUBLE DRILLED FASTENER HOLE WAS DISCOVERED ON THE RH ENGINE DECK (PN: L533M1018346) AND ON THE RH OMEGA STRINGER (PN: L533M1022324). A DETAILED DESCRIPTION OF THE DAMAGE AND AN APPROVED REPAIR PROCEDURE IS PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-EC135-53-2024-1732, ISSUE B DATED 26 JUN 2024.
Part: FRAME — CHAFED (ZONE 100) · airframe 9,374 hrs · 39,449 cycles
CHAFING DAMAGE WAS DISCOVERED ON THE LH SIDE OF FRAME 4A BOX FRAME. A DETAILED DESCRIPTION OF THE DAMAGE AND AN APPROVED REPAIR PROCEDURE IS PROVIDED IN AIR METHODS ENGINEERING AUTHORIZATION 23-5300-EA-4786, INITIAL REVISION DATED 24 JUN 2024 AND IS SUBSTANTIATED BY FAA FORM 8110-3 BY RYAN D. LEE, DER-Y # 905240204, DATED 26 JUN 2024 WITH DER SPECIFIC SEQUENCE # 24RL019AM.
Part: FLOOR SKIN — CORRODED (ZONE 200) · airframe 9,374 hrs · 39,449 cycles
SEVERAL AREAS OF CORROSION AND DENT / DEBOND DAMAGE WERE DISCOVERED ON THE COCKPIT FLOOR UPPER AND LOWER SKIN PANELS (PN: L533M1014217 & L533M1014218). A DETAILED DESCRIPTION OF THE DAMAGE AND AN APPROVED REPAIR PROCEDURE IS PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-EC135-53-2024-2045, ISSUE A DATED 28 JUN 2024.
Part: BEARING — ROUGH (TAIL ROTOR DRIVE) · airframe 23 hrs
DURING A DAILY CHECK OF THE AIRCRAFT A GRINDING NOISE WAS DETECTED FROM THE TAIL ROTOR DRIVESHAFT COVER, AFTER AN INVESTIGATION THE GRINDING NOISE WAS FOUND TO BE COMING FROM THE 2 AFT TAIL ROTOR DRIVESHAFT HANGAR BEARINGS. THE BEARING PN: BB1B649616B, SN: N1899 AND N1828. THE BEARINGS WERE STAMPED (ITALY V) ON THE SIDE. THERE IS NO VISIBLE LOT NUMBER.