N6851X

CESSNA 441 · 1981 · Valid Registration

Registered owner: UPPER PENINSULA AVIATION LLC, MI (owner ≠ operator)

Operators of this aircraft

Who operated this tail, and how firmly we know it.

OperatorRolePeriodBasis
C&C AVIATION LLC (9UPA)Certificate holderMatched by certificate designator

Accident & incident history

No NTSB accidents or incidents on file for this aircraft.

Maintenance disclosures

O · 2013-04-28 Unresolved
ATA 7200

RIGHT ENGINE EGT INCREASED. FIRE LIGHT ACTIVATED AND THEN PERFORMED EMERGENCY SHUTDOWN PROCEDURES.

Source: SDR 2013FA0000325 · FAA SDRS
O · 2006-05-05 Unresolved
ATA 5712

CRACK FOUND DURING ROUTINE CQB 03-1 EDDY CURRENT INSPECTION OF RIGHT UPPER CANTED RIB CAP APPROX 1.5 INCHES FS 179.6. THE UPPER CANTED RIB CAP WAS REPLACED PER CQB 03-1 AND SK441-110B WITH IMPROVED PART 5790066-11. DURING REINSTALLATION OF HI-LOKS AND RIVETS THE UPPER WING TO FUSELAGE CLOSEOUT ANGLE (PART NUMBER 5790066-18) CRACKED APPROX 2 INCHES IN THE RADIUS. THIS PART HAD BEEN INSPECTED PREVIOUSLY AND NO DAMAGE WAS NOTED WHEN THE UPPER CANTED RIB CAP WAS REMOVED. THE CLOSE OUT ANGLE DID NOT APPEAR UNDER ANY EXCESSIVE STRESS WHEN DRAWING DOWN FASTENERS AND RIVETING. FATIGUE IS A POSSIBLE CAUSE. THE RIGHT CLOSE OUT ANGLE WAS REPAIRED PER SK441-110B. THE LEFT WAS ALSO CHANGED/REPAIRED AS A PRECAUTION.

Source: SDR SAI050602 · FAA SDRS
O · 2006-05-05 Unresolved
ATA 5712

DURING THE ROUTINE CQB 03-1 400 HR EDDY CURRENT INSPECTION A CRACK IN THE UPPER LEFT CANTED RIB NEAR THE AFT SIDE OF THE FORWARD MAIN SPAR BEHIND THE HYDRAULIC COMPONENTS AT APPROX FS 179.6. THE CRACK WAS APPOX 1-1.5 INCHES LONG. THE CAP WAS REPLACED PER CESSNA CQB 03-1 AND SK441-110B WITH IMPROVED PART NUMBER 5790066-11. THE WING TO FUSELAGE CLOSE OUT ANGLE WAS REPLACED/REPAIRED AS A PRECAUTION.

Source: SDR SAI050601 · FAA SDRS
O · 2004-01-19 Unresolved
ATA 5730

CORROSION WAS FOUND ON THE RT LEADING EDGE SKIN DURING A ROUTINE DE-ICE BOOT CHANGE. IT WAS FOUND ON THE OUTER PORTION LOWER SIDE OF THE SKIN. THE CORROSION WAS OF SUCH A DEPTH AFTER ITS REMOVAL THAT REPAIRS WERE REQUIRED. THE MOST LIKELY CAUSE IS POOR BOOT INSTALLATION LEAVING GAPS IN THE ADHERING SURFACES. THIS MAY HAVE ALLOWED THE AREAS TO FORM CONDENSATION BETWEEN THE BOOT AND SKIN AND OVER THE DE-ICE BOOTS 7+YEARS OF SERVICE.(K)

Source: SDR EAT2004F00001 · FAA SDRS