N436PA
Registered owner: BIRD ACQUISITION LLC, AZ (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| BIRD ACQUISITION LLC | Operator | on 2013-07-05 | Operator named in NTSB report |
Accident & incident history
Operated by Bird Acquisition LLC (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.
6 reports on file, 2012-01-04 – 2016-01-25.
Part: BULKHEAD — CRACKED (ZONE 200) · airframe 7,995 hrs
DURING A ROUTINE INSPECTION, CRACKS WERE NOTED IN A BULKHEAD IN THE AFT UPPER FUSELAGE ADJACENT TO THE DORSAL FIN FORWARD ATTACH FITTING. THE CRACKS WERE MADE VISIBLE BY REMOVAL OF THE FAIRING THAT COVERS THE FORWARD ATTACH FITTING. FURTHER INSPECTION OF THE BULKHEAD AFTER IT WAS REMOVED, REVEALED IT WAS CRACKED IN 2 PLACES- THE OTBD MOST RIVET HOLES, LT AND RT, THAT ATTACH IT TO THE PN 78965-007 DOUBLER. CRACKS RADIATED OUTWARD FROM EACH RIVET HOLE AND A CRACK WAS SEEN IN THE INNER RADIUS OF THE FLANGE AT THE BULKHEAD'S TOP. NO CORROSION WAS PRESENT ON THE BULKHEAD OR ANY ADJACENT PARTS. IT IS SUSPECTED THAT INFLIGHT STRESSES IMPOSED ON THE DORSAL FIN TRANSFERRED TO THE BULKHEAD AND INSTIGATED THE CRACKING.
Part: DOUBLER — CRACKED (BULKHEAD) · airframe 7,995 hrs
THE AFT FUSELAGE BULKHEAD, HAD BEEN FOUND CRACKED AND WAS IN THE PROCESS OF BEING REPLACED. WHEN THE BULKHEAD WAS REMOVED, THE DOUBLER, SUBJECT OF THIS REPORT, WAS FOUND TO HAVE NUMEROUS CRACKS AS WELL. CRACKS WERE CONCENTRATED IN THE 2 OTBD TOP RIVET HOLES, SAME AS THE BULKHEAD IT WAS RIVETED TO, AND HAD MULTIPLE CRACKS IN EACH LOCATION. NO CORROSION WAS PRESENT. IT IS SUSPECTED IN FLIGHT LOADS IMPOSED ON THE DORSAL FIN INSTIGATED THE CRACKING IN THE BULKHEAD AND DOUBLER.
Part: ANGLE — CRACKED (ZONE 600)
DURING A PROGRESSIVE INSPECTION, AN ANGLE IN THE RT WING WAS FOUND TO BE CRACKED BEHIND THE LANDING GEAR SIDE BRACE FITTING. THE CRACKED ANGLE HAD BEEN INSTALLED IAW SB1161 AND WAS CONTAINED IN KIT PN 767-398.
Part: ANGLE — CRACKED (ZONE 500) · airframe 7,752 hrs
DURING A PROGRESSIVE INSPECTION, AN ANGLE IN THE LT WING WAS FOUND TO BE CRACKED BEHIND THE LANDING GEAR SIDE BRACE FITTING. THE CRACKED ANGLE HAD BEEN INSTALLED IAW SB 1161 AND WAS CONTAINED IN KIT PN 767-397.
Part: ANGLE — CRACKED (RT NACELLE)
DURING A SCHEDULED INSPECTION, A CRACK WAS FOUND IN THE NACELLE ANGLE. UPON FURTHER INVESTIGATION, IT WAS FOUND THAT THE CRACK WAS BETWEEN THE 2 RIVETS THAT EXTENDED THRU THE WING SKIN INTO CAP (P/N 67097-002 OR -003 DEPENDENT ON SIDE) WHICH IS ATTACHED TO A WEB (PN 67079-000 OR 001 DEPENDENT ON SIDE) THAT THE MAIN GEAR AFT ATTACH POINT IS MOUNTED. IT IS SUSPECTED THAT THIS IS A FAILURE DUE TO FATIGUE.
Part: ANGLE — CRACKED (LT NACELLE)
DURING A SCHEDULED INSPECTION, A CRACK WAS FOUND IN THE NACELLE ANGLE. UPON FURTHER INVESTIGATION, IT WAS FOUND THAT THE CRACK WAS BETWEEN THE 2 RIVETS THAT EXTENDED THRU THE WING SKIN INTO CAP (P/N 67097-002 OR -003 DEPENDENT ON SIDE) WHICH IS ATTACHED TO A WEB (PN 67079-000 OR 001 DEPENDENT ON SIDE) THAT THE MAIN GEAR AFT ATTACH POINT IS MOUNTED. IT IS SUSPECTED THAT THIS IS A FAILURE DUE TO FATIGUE.