N611SJ
Registered owner: ASPIRUS WAUSAU HOSPITAL INC DBA, WI (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
DURING INSPECTION, THE COCKPIT FLOOR UPPER SHEET (PN: B531M8020201) AND LOWER SHEET (PN: B531M8021201) ARE DAMAGED IN THE FORM OF CORROSION AT THE LOCATIONS OF THE FWD GROUNDING POINTS. THE CORROSION AREAS FOR THE UPPER SHEET WERE MEASURED TO BE APPROXIMATELY 1.0â X 1.0â. THE CORROSION AREA FOR THE LOWER SHEET WAS MEASURED TO BE APPROXIMATELY 1.0â X 0.50â. DESCRIPTION OF WORK: REPAIRED THE DAMAGE IN ACCORDANCE WITH AIRBUS REPAIR DESIGN APPROVAL RDAS-BK117-53-2022-0123 ISSUE A DATED 20 JAN 2022. APPROVED DATA: RDAS-BK117-53-2022-0123 ISSUE A DATED 20 JAN 2022 IS EASA APPROVED (DOA EASA.21J.700). IAW THE FAA AND EASA BILATERAL AGREEMENT AND TECHNICAL IMPLEMENTATION PROCEDURES, THE FAA CONSIDERS THE DATA FAA APPROVED.
DURING INSPECTION, FOUND DAMAGE IN THE FORM OF CORROSION TO THE STA1672.5 FRAME WEB (PN: B531K1323-209), FRAME 1 DESCRIPTION OF WORK: REPAIRED THE DAMAGE IN ACCORDANCE WITH AIRBUS REPAIR DESIGN APPROVAL RDAS-BK117-53-2022-0134A ISSUE A DATED 20 JAN 2022. APPROVED DATA: RDAS-BK117-53-2022-0134A ISSUE A DATED 20 JAN 2022 IS EASA APPROVED (DOA EASA.21J.700). IAW THE FAA AND EASA BILATERAL AGREEMENT AND TECHNICAL IMPLEMENTATION PROCEDURES, THE FAA CONSIDERS THE DATA FAA APPROVED.
DURING INSPECTION, FOUND THE RH FRAME 4 INNER SKIN (PN: B533K5605-203) IS DAMAGED IN THE FORM OF DISCREPANT HOLES FROM THE INSTALLATION OF AN INTERIOR PANEL BRACKET. THERE ARE 2EA DISCREPANT HOLES NEAR THE FWD EDGE OF THE INNER SKIN. DESCRIPTION OF WORK: FOLLOWED AIRBUS RDAS -BK117-53-2022-0170 AND BLENDED THE DAMAGE TO SMOOTH CONTOURS REMOVING THE MINIMUM AMOUNT OF MATERIAL NECESSARY. FABRICATED A REPAIR DOUBLER (PN: RDAS-BK117-53-2022-0170.01) USING A MINIMUM OF 0.020âTHICK 301 ¼ HARD, OR HARDER, STAINLESS STEEL). SIZE THE DOUBLER TO ACCOMMODATE THE INSTALLATION OF THE FASTENER PATTERN. CONTOURED THE DOUBLER TO MATCH THE PROFILE OF THE INNER SKIN. RADIUS ALL DOUBLER CORNERS TO A MINIMUM OF 0.25â. PILOT DRILL FOR NEW FASTENER LOCATIONS ENSURING A MINIMUM OF 2D ED AND 4D â 8D PD. APPLIED SEALANT TO THE FAYING SURFACES OF THE REPAIR DOUBLER AND AIRCRAFT. IN EXISTING LOCATIONS, INSTALLED FASTENERS OF THE SAME TYPE AND SIZE AS WERE ORIGINALLY INSTALLED. IN ALL NEW FASTENER LOCATIONS, INSTALLED MS20470AD4 RIVETS (ALTERNATIVELY, INSTALL CR3213-4 BLIND RIVETS). INSTALLED ALL FASTENERS WET, AND ALLOW THE SEALANT TO CURE PER THE MANUFACTURERâS INSTRUCTIONS
IN CRUISE FLIGHT, PILOT AND CREW NOTED A BANG, FOLLOWED BY APPROX 45 SEC TO ONE MINUTE OF VIBRATION. VIBRATION WENT AWAY, AIRCRAFT WAS SAFELY LANDED AT KONA (WINONA MUNICIPAL AIRPORT). UPON POST FLIGHT WALK AROUND, DAMAGE TO YELLOW MR BLADE WAS OBSERVED AND THE MR HUB CAP WAS FOUND TO BE MISSING.
TAIL ROTOR GEARBOX CHIP LIGHT CAME ON IN-FLIGHT ACCOMPANIED WITH A HIGH PITCH INTERMITTENT SQUEAL. TOOK THREE ATTEMPTS WITH FUZZ BURNER SYSTEM TO EXTINGUISH THE LIGHT. FAILURE OF ONE OF THE INTERNAL BEARINGS OF THE 90 DEGREE GEARBOX. FOUND CHIP PLUG FULL OF METAL FLAKES. INSTALLED SERVICEABLE T/R GEARBOX, PN 222-042-001-007, S/N AMS-50036, AND T/R HUB AND BLADES, P/N 222-012-701-107, S/N A235. BLADE, P/N 222-016-001-111, S/N A390 AND A387, T/R DRIVE SHAFT HANGER BEARING ASSY 222-044-003-101, S/N A20-00608.