N473CW
Registered owner: ALFA FOX X LLC, FL (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| Pentastar Aviation Charter, Inc. (UG8A) | 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.
4 reports on file, 2002-09-24 – 2016-02-11.
Part: ATTACH FITTING — WORN (VERTICAL STAB) · airframe 9,341 hrs · 4,951 cycles
THE LT RUDDER ATTACH POINT NR 3, LOWER BORE ON THE VERTICAL STABILIZER IS WORN BEYOND NOMINAL SIZE. OVERSIZED HOLE OF LT LOWER RUDDER FITTING OF VERTICAL STABILIZER TO FIRST OVERSIZE 0.3125", IAW DWG SE05000102 REV. INITIAL DATED 8 11 2015 WITH FAA APPROVAL ON FAA FOR 8100-9 BY ODA-511131-CE DATED 2 10 2016.
Part: FITTING — WORN (VERTICAL STAB) · airframe 9,341 hrs · 4,951 cycles
THE LEFT RUDDER ATTACH POINT NR 3, LOWER BORE ON THE VERTICAL STABILIZER, IS WORN BEYOND NOMINAL SIZE. OVERSIZED HOLE OF LT LOWER RUDDER FITTING ON VERTICAL STABILIZER TO FIRST OVERSIZE .3125" IAW DWG SE05000102 REVISION INITIAL DATED 8 112015 WITH FAA APPROVAL ON FAA 8110-9 BY ODA-511131-CE DATED 2 10 2016.
Part: HINGE FITTING — WORN (RT ELEVATOR) · airframe 9,341 hrs · 4,951 cycles
THE RIGHT ELEVATOR HINGE NR 4 FITTING WAS PREVIOUSLY OVERSIZED WITH A REPAIR BUSHING, THE FITTING ATTACH HOLES BOTH UPPER & LOWER ARE ELONGATED & TAPERED. ENLARGED TWO EACH BORES IN THE RT ELEVATOR NR 4 HINGE FITTING TO SECOND OVERSIZE & ENLARGED UPPER & LOWER NR 4 HINGE BORES ON THE HORIZONTAL STABILIZER TO SECOND OVERSIZE IAW DWG SE05000102 REV. INITIAL DATED 8 11 2015 WITH FAA APPROVAL ON FAA FOR 8100-9 BY ODA-511131-CE DATED 2 10 2016.
Part: COUPLING — LOOSE (HYD SYSTEM)
THE FLIGHT CREW NOTED A COMBINED HYDRAULIC SYSTEM FAILURE MESSAGE. THE SYSTEM LOST PRESSURE DUE TO FLUID STARVATION AT THE SUPPLY LINE TO THE HYDRAULIC PUMP ON THE LEFT ENGINE. THE QUICK DISCONNECT COUPLING APPARENTLY HAD NOT BEEN LOCKED INTO PLACE. THE QUICK DISCONNECT WAS RELOCKED AND TESTED. NO DEFECTS NOTED. THE HYDRAULIC SYSTEM WAS INSPECTED AND TESTED USING G-IV MM RECOMMENDATIONS. NO DEFECTS WERE NOTED. THE SYSTEM WAS THOROUGHLY TESTED. NO DEFECTS NOTED. THE AIRCRAFT WAS RETURNED TO SERVICE. (M)